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Symphony Aircfraft POH

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1. CONDITIONS ZERO WIND ISA WEIGHT 975 kg 2150 Ibs INITIAL FUEL LEAN MIXTURE UP TO 75 POWER FOR BEST LOADING 110 LITERS 29 1 U S GAL USABLE ECONOMY AND ADJUST FULL RICH ABOVE 7556 12 000 10 000 o E PH LI 8000 we fra LLI Q 2 E 6000 5 lt LLI tc 2 Ka 4000 LLI tr D a a a 2000 x E z R 3 1 5 2 2 5 3 3 5 4 ENDURANCE HOURS NOTE ENDURANCE INCLUDES FUEL FOR START TAXI CLIMB AND DESCENT WITH 45 MINUTES RESERVE AT CRUISE POWER AND TIME FOR CLIMB Figure 5 11 Feb 25 2005 5 23 SECTION 5 Symphony PERFORMANCE SA 160 LANDING DISTANCE FOR SHORT FIELDS CONDITIONS WEIGHT 975 kg 2150 Ibs APPROACH SPEED AT 50 FT 65 KIAS FLAPS 40 PAVED DRY RUNWAY ZERO WIND ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C Total Total Total Total Total Pressure to to to to to Altitude Clear Ground Clear Ground Clear Ground Clear Ground Clear Ground ft 50 ft Roll 50 ft Roll 50 ft Roll 50 ft Roll 50 ft Roll OBS ft OBS ft OBS ft OBS ft OBS ft ft ft ft ft ft MSL 2182 869 2280 902 2346 935 2395 968 2461 1001 1000 2264 902 2329 935 2395 968 2461 1001 2526 1033 2000 2313 935 2379 968 2444 1001 2510 1033 2575 1066 3000 2379 951 2444 984 2510 1033 257
2. Tunc Figure 4 1 Feb 25 2005 4 5 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 EE pes aae aA rE AEE CHECK BATS WIth waza ste napa tics ON TEST aani CHECK Flaps EXTEND Yellow Light Flaps in Motion CHECK Landing Light at Night trt tenentes CHECK Strobe Light at Night ssania ania ki trier inerte tone CHECK NAW Light at Night eerte eee tenet CHECK Instr Map Lights at Night eee etes CHECK BAT Switch tre tpe Er X ERO HERREN OFF 2 Left Wing Fuel Tank SUMP ai DRAIN fuel into clear cup Fuel CHECK for water sediment and proper fuel Left Main Gear Strut and Wheel Fairing CHECK Main Wheel Tirevcinn asis beris CHECK for proper inflation and general condition Wing SUGTACE uec rnnt ret FREE of ICE FROST SNOW Left Side Top Deck Hatch sisisi CHECK for security 20 Flap Position Color Marking on Flap Track CHECK for condition Flap and AGET N aw CHECK for freedom of movement and security Bonding Straps CHECK for security of attachment and general conditions Static Dischargers CHECK for security of attachment and general conditions Counter Weight oce CHECK for security of attachment Wing Tip and Lights sa aan wa EA CHECK Wing
3. anony SECTION 6 SA 160 WEIGHT AND BALANCE WEIGHT AND MOMENT LIMITS WEIGHT Ibs a a i E o 3 R 8 8 8 8 8 8 8 LN 4 R a s 4 o 4 o a O N O 4 2 o E S O 34 O z z l l z lt T uj m m Q H Bc e B O 7 ARE Tm O J T q 8 2 m T m m m H Z 4 m O z m O U y Si B c lt Le C J Z z ol L ep8Se8 BB 288 8 82 88 22 8 o o o eo o o eo eo o o o o o o o o o WEIGHT kg Figure 6 7 Feb 25 2005 6 13 SECTION 6 gt ymphony WEIGHT AND BALANCE SA 160 6 8 WEIGHT AND BALANCE EXAMPLE The following example is provide as a guide for weight and balance calculation and does not reflect a specific aircraft The weight and balance data specific to each aircraft must be performed before each flight Assuming the following basic data we have Basic empty weight 1470 Lbs Empty weight moment 1449 32 in lbs 100 C of G Empty 98 6linches From the following aircraft loading information we have Pilot 200 Ibs Passenger 185 lbs Baggage area 1 60lbst HE Baggage area 2 40lbs Fuel 20 USG Using the Weight and Balance Loading Graph of Figure 6 4 and the data of Figures 6 5 and 6 6 we obtain the weight and balance data shown in Figure 6 8 In the example the center of gravity location at take off is found to be Cof G o 199510 in Ibs 1966 Ibs 101 5in This point is found to be within the envelope of the graph Weight and Moment Limit
4. CHECK for water Cabin BAT wird C M EG ON 4 8 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES Papo EE RETRACT BAT SWit ls eege Eeer OFF b Before Starting Engine Preflight Check cin ia COMPLETE BAT SWiteli inei A AA ti Ete UR Ree ER ON Cabin Lighting at Night AS REQUIRED Fuel Quantity iet eene centered taie SUFFICIENT Seat Belts and Harmnesses FASTENED CHECK Eelere a CLOSED LATCHED Charts Navigation Equipment and Flashlight at Night cocinan ON BOARD AVIONIC 1 AVIONIC 2 IFR Gwitches sese OFF Fuel Valve deci an CHECK ON c Starting Cold Engine BEAK CS caninas opea PERO G E IEEE IS SET ALD Switch tia Aoki ino paki cii ON INST LT MAP LT Dimmer Switches at Night 111 1 ON DOME ET Switch at Night wena OO rhe Pieter OFF STROBE LT Switch awaits pino ON Carburetor Eleat sca ze A OFF Throttle iere reete 6 mm 1 4 in OPEN MUE FULL RICH PAMET iria ONE TO THREE STROKES Propeller ATCA ooo wodna dia Nan RAA CLEAR Ignition OWIEC ere reet EI ow START Throttle aaa die or ore erae REGE ADJUST to 1000 1200 RPM Oil pressure icon iia ciae da aide ai CHECK NAV LT Switch at Night iter tiri teint ZAL AE ON Feb 25 2005 4 9 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 d Starting Hot Engine lucir SET ALT SW EE ON STROBE LI Switch eei tree nicas ON Carburetor Heat rca danita caia OFF
5. 3 6 g Ditching insieme eee ertet 3 6 h Engine Fire During Gtart sss 3 7 i Engine Fire In Flight ainia 3 7 j Electrical Fire In Flight cocina 3 8 k Loss Of Oil Pressure aaa a Ea 3 8 D Power Supply System Malfunction sese 3 9 m Excessive Rate Of Charge aaa sac 3 9 M Uta eege 3 9 o Flap Actuator Drive Failure sese 3 9 p Static Source Blockage OUER 3 10 q Spin Recovery Drocedure esee 3 10 3 7 Amplified Emergency Drocedures esses 3 11 Engine Failure During Takeoff Roll 3 5 a 3 11 Engine Failure Immediately After Takeoff 3 5 b 3 11 Engine Failure During Flight 3 5 c sss 3 12 Landing Without Engine Power 3 5 d sss 3 13 Rough Engine Operation OBei sss 3 14 Feb 25 2005 3 1 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 TABLE OF CONTENTS Continued Precautionary Landing With Engine Power 3 5 f 3 14 Ditching 3 5 AAA Of 3 15 Engine Fire During Start 3 5 h eee 3 15 Engine Fire In Flight 3 5 1 ai 3 16 Electrical Fire In Flight 3 5 aaa A NAA EA 3 16 Loss Of Oil Pressure 3 5 K iacere enti irre 3 17 Power Supply System Malfunction OI 3 18 Excessive Rate Of Charge 3 5 m sse 3 18 Icing 3 50 E M Q 3 19 Static Source Blockage IFR 3 5 p sss 3 20
6. eee 7 56 Feb 25 2005 7 3 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 INTENTIONALLY LEFT BLANK 7 4 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 7 1 GENERAL This section describes the operation of the aircraft with its equipment and its systems The user should become familiar with the aircraft system operation to ensure optimal and secure usage of the aircraft The content of this section refers to a standard SA 160 aircraft Description and operation of optional equipment is described in the Section 9 under SUPPLEMENTS 7 3 AIRCRAFT The SA 160 is a single engine high wing aircraft equipped with fixed tri cycle landing gear and designed for general utility operation The cabin provides comfortable side by side seating for two people with dual flight control 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 good visibility Entry to and exit from the aircraft is effected througha door on each side of the cabin The rectangular wings are dihedral and strut braced Fowler flaps extend from the trailing edge up to the ailerons and along to the wing tips At the outboard portion of each wing on the top side two Vortex Generators are installed They increase the effectiveness of the ailerons at high angle of attack near the aircra
7. CHECK LOCKED Ignition Switch certet teneas L then R then BOTH If operation is satisfactory on either magneto continue on that magneto to first suitable airfield Engine Parameters a derio ida CHECK If roughness continues for some minutes and atmospheric conditions make carburetor icing unlikely Carburetor Heat ao ad an O tete ius OFF Feb 25 2005 3 5 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 f g 3 6 Precautionary Landing With Engine Power 1 Locate suitable field Test suitability of the field with overflight If radio contact is available inform the corresponding ground station about intentions and location N 3 Prepareforlandingapproach In final turn 4 PSUS POO wiz z ai endi Ana 65 KIAS KT 40 6 Seat Belts and Harnesges E TIGHT Before landing 7 SowWatch H EN KE OFF 8 Cabin Doors UNLATCH PRIOR TO TOUCHDOWN 9 After touchdown with lowest possible airspeed apply brakes and attempt to avoid obstructions if possible TU MIKU e usina colas IDLE CUT OFF TL Ignition S Witch ninia nina OFF 12 Fuel Valve ceci terr E OFF Ditching After an engine failure immediately secure glide speed 74 KIAS trim aircraft When the mainland can t be reached 1 Transmit Mayday message giving location and intentions set Squawk 7700 or as directed by TC Perform approach into the wind if strong winds and heavy seas otherwise parallel to swells Seat Belts and Harnesses sss TIG
8. 2 Operation The VM 1000 Indicator To set the VM 1000 engine management system in operation place the BAT switch in ON position After power up the system is ready for flight Five control buttons are located below the VM 1000 indicator Refer to figure 7 6 for a quick reference To change graphic sweep display formats simply hold BUTTON 3 in during power up until the display begins showing actual parameters and is operating The diamond graph display in the lower left corner of the VM 1000 indicator has two display modes Normal Modes 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 observed A defective CHT or EGT probe will leave the respective graph blank A flashing CHT graph indicates a cylinder is too hot or is being shock cooled The digital display below the diamond graph system shows in the default mode the number of the cylinder that leaned before any other during leaning mode ex P1 means cylinder 1 and the hottest cylinder ex H3 means cylinder 3 By pressing BUTTON 2 one can select other cylinders Then the display will show temperatures for each EGT and CHT pair and periodically the cylinder number Feb 25 2005 7 25 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 Brackets 7 26 LeaningMode Leaning mode is selected by pressi
9. SUPPLEMENT 1 TABLE OF CONTENTS SECTION PAGE GENERAL ae E EEN en EN 2 of 16 LIMITATIONS 5 5 ek e ym y a de UR qm 3 of 16 EMERGENCY PROCEDURES 5 of 16 NORMALPROCEDURES 6 of 16 PERFORMANCE proa um RR ERR ERR 9 of 16 WEIGHT AND BALANCE 9 of 16 DESCRIPTION AND OPERATION 10 of 16 Feb 25 2005 1 of 16 SECTION 9 ymphony SUPPLEMENT 1 SA160 SECTION 1 GENERAL 1 1 INTRODUCTION The GNS 430 System is a fully integrated panel mounted instrument which contains a VHF Communications Transceiver a VOR ILS receiver and a Global Positioning System GPS Navigation computer The primary function of the VHF Communication portion of the equipment is to facilitate communication with Air Traffic Control The primary function of the VOR ILS Receiver portion of the equipment is to receive and demodulate VOR Localizer and Glide Slope signals The primary function of the GPS portion of the system is to 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 s position velocity and time 1 2 SPECIFICATIONS Provided the GARMIN GNS 430 s GPS receiver is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications for a VFR IFR enroute terminal and non precision instrument approach GPS L
10. b AVIONIC Switches The AVIONIC 1 and AVIONIC 2 IFR switches are located on the left part of the instrument panel right to the ALT BAT switch They control the flow of current to the avionic bus 1 and the avionic bus 2 IFR For IFR equipped aircraft the bus 1 and bus 2 switches provide the option to remove power supply from the avionic buses separately This provides the capability to disconnect nonessential electrical accessories in the event of an alternator failure CAUTION fp To avoid damage to the avionics equipment the AVIONIC power switches should be placed in the OFF position prior to turning the ALT BAT switch ON or OFE starting the engine or applying an external power source c Indicating and Warning Devices Ammeter The ammeter is integrated in the VM 1000 Engine Management System The amperage is displayed on the VM 1000 indicator in the lowerrightarea both graphically and digitally See Fig 7 6 The ammeter system functions as an alternator load meter displaying current flow from the alternator to aircraft electrical system Additionally the system has a built in warning that is coupled with the EC 100 When the alternator does not produce enough power for the electrical system the EC 100 will automatically begin to flash the warning AMPS TO LOW and a pulsing audio tone will be present 7 40 Feb 25 2005 Symphony Atte SECTION 7 SA 160 DESCR amp OPERATION Ammeter Se
11. sse 4 32 r After Engine Shut Down 4 5r sss 4 32 4 2 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES 4 1 GENERAL This section contains the normal operating procedures for the aircraft All of the normal operating procedures required by the Aviation Authorities as well as those necessary for operation of the aircraft as determined by the operating and design features of the aircraft are presented Normal operating procedures associated with optional systems and equipment which require handbook supplements are presented in Section 9 Supplements This section should put the pilot in a position to use the aircraft and or its systems and equipment optimally and safely Therefore it is recommended to make yourself familiar with the procedures and be able to master them This section is divided into two main parts 1 The first part contains the normal procedure checklists These checklists are clearly arranged to give an action sequence for normal procedures with little emphasis on the operation of the systems 2 The second part provides amplified normal procedures corres ponding to the normal procedures checklist items These amplified normal procedures contain detailed information and explanations of the procedures and how to perform them This portion of the section is not intended for use in flight The numbers located in parentheses after each paragraph heading indicate th
12. This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and TC Approved Airplane Flight Manual when the GARMIN GTX 327 Iransponder has been installed The Information contained herein supplements or supersedes the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Date 4 rect Approved Transport Canada lp aa Issued Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 4 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective 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 2005 i Feb 25 05 ii Feb 25 05 1of 8 Feb 25 05 2 of 8 Feb 25 05 3 of 8 Feb 25 05 4 of 8 Feb 25 05 5 of 8 Feb 25 05 6 of 8 Feb 25 05 7 of 8 Feb 25 05 8 of 8 Feb 25 05 Feb 25 2005 i Symphony SECTION 9 IRCRAFT SUPPLEMENT 4 SA160 LIST OF REVISIONS Rev Page s Na Date No Description ii Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 4 SUPPLEMENT 4 TABLE OF CONTENTS SECTION PAGE GENERAL es isso pu a wawa ai 2 of 8 LIMITATIONS 5 44 e ex BASSES Ge ee YA 3 of 8 EMERGENCY PROCEDURES 3 of 8 NORMAL PROCEDU
13. c Rotate the small left knob to select the desired kilohertz KHz value d To activate the selected frequency press the corresponding flip flop key i for COM frequencies or for VLOC frequencies 4 3 DATA ENTRY a Data is entered in the GPS window using the large and small right knobs The large right knob ke js used to move the cursor about the page The small right knob is used to select individual characters for the highlighted cursor location 4 4 PAGE SELECTION a Selection of any main page is performed using the large and small right knobs The large right knob selects the page group NAV WPT or AUX The small right knob selects the desired page within a group To quickly select the default NAV page pressand hold CB Feb 25 2005 9 of 16 SECTION 9 ymphony SUPPLEMENT 1 SA160 4 5 TO SELECT A DIRECT TO DESTINATION a Press the key A select direct to waypoint page will appear with the waypoint identifier field highlighted b Use the small and large A right knobs to enter the identifier of the desired destination waypoint c Press E to confirm the selected waypoint and ZB toactivate the direct to function 4 6 TO SELECT A NEARBY AIRPORT AS A DIRECT TO DESTINATION a Press to display the select direct to waypoint page b Rotate the large right knob 8 nearest airport NRST field to place the flashing cursor on the c Rotate the small right knob 6 nine neares
14. 5 10 Feb 25 2005 Symphon Y SECTION 5 SA 160 PERFORMANCE AIRSPEED CALIBRATION Alternate Static Source CONDITIONS COCKPIT VENTILATION OFF Normal KIAS 130 140 150 160 Alternate KIAS 129 140 151 161 NOTES 1 INFLUENCE OF VENTILATION WITH THE COCKPIT VENTILATION OPEN ONE OR TWO FRESH AIR NOZZLES THE VALUES IN THE ALTERNATE KIAS COLUMN DECREASE BY 0 5 KT 2 INFLUENCE OF THE CABIN HEAT IS FOUND TO BE NEGLIGEABLE EXAMPLE DESIRED AIRSPEED 70 KIAS AIRSPEED INDICATOR READING 73 KIAS Figure 5 1 2 Feb 25 2005 5 11 SECTION 5 gt ymphony PERFORMANCE S 160 ALTIMETER CORRECTION CONDITIONS MSL KIAS AND INDICATED ALTITUDE ASSUME ZERO INSTRUMENT ERROR CORRECTION TO BE ADDED FEET CONDIIION te 55 60 6 70 80 90 105 115 125 pi 40 An un An An 10 15 0 410 FLAPS uw mm on 6 5 0 20 FLAPS W 0 6 6 6 0 40 EXAMPLE FLAPS 0 INDICATED AIRSPEED 95 KIAS ALTIMETER CORRECTION 10 ft Figure 5 2 1 5 12 Feb 25 2005 Symphon Y SECTION 5 SA 160 PERFORMANCE ALTIMETER CORRECTION Alternate Static Source CONDITIONS MSL COCKPIT VENTILATION OFF KIAS 60 70 80 90 100 110 120 130 140 150 160 CORRECTIONTOBE 40 05 40 50 70 70 90 110 130 145 165 NOTES 1 INFLUENCE OF VENTILATION WITH THE COCKPIT VENTILATION OPEN ONE OR TWO FRESH AIR NOZZLES ADD TO THE VALUES IN THE CORRECTION TO BE ADD
15. Changes between the specified points are linear The reference datum is 1 5367 m 60 5 in in front of the firewall Statements for correct loading see also in section 6 Weight and Balance 2 15 MANEUVER LIMITS All aerobatics maneuvers including spins are prohibited The aircraft is authorized for maneuvers in which the angle off bank is not more than 60 2 6 Feb 25 2005 Symphon Y SECTION 2 SA 160 LIMITATIONS 2 17 FLIGHT LOAD FACTOR LIMITS Configuration Maximum Flight Load Factor Flaps Up 3 80 1 5 Flaps Down 2 00 Maneuvers with a negative flight load factor are prohibited 2 19 CREW a Minimum Crew VFR 1 Pilot b Minimum Crew IFR 1 Pilot FAA registered Aircraft c Max Persons on Board 2 Pilots operating aircraft of other than U S registry should refer to the appropriate regulations of the country of certification 2 21 KINDS OF OPERATIONS The aircraft is certified for VFR Day Night and IFR operations as long as the equipment required by FAR Part 91 is installed and operational Flightinto known or forecasticing conditionsis prohibited The reference to types of flight operations on the operating limitation placard reflects equipment installed at the time of Airworthiness Certificate issuance Feb 25 2005 2 7 SECTION 2 gt ymphony LIMITATIONS SA 160 2 23 FUEL LIMITATIONS a Total Fuel 1221 32 2 U S Gallons b Usable Fuel 1101 29 1 U S Gallons c Unusable Fuel
16. 121 3 1U S Gallons Additional Fuel Limitations a With less than 12 liters 3 U S Gallons per each wing tank Indicator shows Lo power on descents with flaps fully extended must be limited to maximum 10 minutes duration 2 25 OTHER LIMITATIONS a Airframe For safe aircraft operation all four Vortex Generators Refer to Section 7 7 3 Aircraft must be in place and in good condition WARNING ty Absence of one or several Vortex Generators affects the flight behavior of the aircraft unfavorably when close to the stall speed 2 27 TEMPERATURE LIMITATION a OAT for Operating Avionics 20 50 C 2 8 Feb 25 2005 Symphon Y SECTION 2 SA 160 LIMITATIONS 2 29 PLACARDS The following placards must be attached inboard and outboard of the aircraftin the required places 1 In full view of the pilot WITH FUEL BELOW 12 LITERS 3 U S GAL IN EACH WING TANK Lo IND POWER ON DESCENTS WITH FLAPS DOWN ARE LIMITED TO 10 MINUTES MAX DURATION SEE POH OPERATING MODE NORMAL CATEGORY FOR FLIGHTS IN VFR DAY AND NIGHT CERTIFIED FLIGHTS INTO KNOWN ICING CONDITIONS ARE PROHIBITED FLIGHTS IN HEAVY TURBULENT AIR AND CLOSE TO THUNDERSTORMS ARE PROHIBITED SEE THE LIMITATION SECTION IN THE POH MAXIMUM GROSS WEIGHT 2150 Ibs MAXIMUM LANDING WEIGHT 2042 Ibs MANEUVERING SPEED 116 kts For VER MAX FLAP EXTENDED SPEED 90 kts MAX DEMONSTRATED CROSSWIND e equippe
17. 14 of 15 Feb 25 2005 Symphony SA160 b Screen Areas Map Display COM Window Data User Selectable Fields Data Field Map Scale Map Page Present Position Desired Track Figure 7 2 Screen Areas Map Page c NavData Card Slots There are two data card slots on the face of the GNC 420 The Jeppesen NavData card should be inserted in the left most slot The second slotis provided for future options and expansion capabilities Insert the card with the swing arm handle at the bottom and the label facing to left Feb 25 2005 15 of 15 Symphony SA160 Symphony uu Airplane Flight Manual Supplement Model SA 160 SUPPLEMENT 3 GARMIN GMA 340 AUDIO PANEL This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and TC Approved Airplane Flight Manual when the GARMIN GMA 340 Audio Panel has been installed The Information contained herein supplements or supersedes the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Date 4 rect Approved Transport Canada lp aa Issued Feb 25 2005 Symphony AIRCRAFT SA160 SECTION 9 SUPPLEMENT 3 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective pages in the Supplement as well as t
18. 2005 6 13 Feb 25 2005 7 31 Feb 25 2005 6 14 Feb 25 2005 7 32 Feb 25 2005 7 1 Feb 25 2005 7 33 Feb 25 2005 7 2 Feb 25 2005 7 34 Feb 25 2005 7 3 Feb 25 2005 7 35 Feb 25 2005 Feb 25 2005 V Symphony IRCRAFT LOG OF EFFECTIVE PAGES SA 160 PAGE DATE PAGE DATE 7 36 Feb 25 2005 8 15 Feb 25 2005 7 37 Feb 25 2005 8 16 Feb 25 2005 7 38 Feb 25 2005 8 17 Feb 25 2005 7 39 Feb 25 2005 7 40 Feb 25 2005 7 41 Feb 25 2005 7 42 Feb 25 2005 7 43 Feb 25 2005 7 44 Feb 25 2005 7 45 Feb 25 2005 7 46 Feb 25 2005 7 48 Feb 25 2005 7 49 Feb 25 2005 7 50 Feb 25 2005 7 51 Feb 25 2005 7 52 Feb 25 2005 7 53 Feb 25 2005 7 54 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 2005 8 12 Feb 25 2005 8 13 Feb 25 2005 8 14 Feb 25 2005 vi Feb 25 2005 Symphony AIRCRAFT SA 160 LOG OF EFFECTIVE PAGES Feb 25 2005 INTENTIONALLY LEFT BLANK vii Symphony IRCRAFT LOG OF EFFECTIVE PAGES SA 160 INTENTIONALLY LEFT BLANK viii Feb 25 2005 Symphony AIRCRAFT SA 160 LIST OF REVISIONS LIST OF REVISIONS Rev Date Page No No Description Approval Feb 25 2005 ix Symphony IRCRAFT LIST OF REVISIONS SA 160 INTENTIONALLY LEFT BLANK x Feb 25 2005 Symphony IRCRAFT SA 160 CONTEN
19. Feb 25 2005 7 of 15 SECTION 9 Symyhon ZONY SUPPLEMENT 2 SA160 5 Time To 4 minutes 6 Distance to 10 0 nm 7 Ground Speed 150 kts 8 Ext Annunciators ON c Once the self test concludes the database page will appear showing the effective and expiration dates of the Jeppesen database on the NavData card d Press to acknowledge the database page and proceed to the instrument panel self test page f Rotate the small right knob to select the desired page in the NAV Group 4 2 COM FREQUENCY SELECTION a Rotate the large left knob O Q to select the desired megahertz MHz value b Rotate the small left knob to select the desired kilohertz KHz value c To activate the selected frequency press the flip flop key 4 3 DATA ENTRY a The GPS window cursor is used to select the desired fields Press the small right knob to O the cursor Press again to deactivate it The large right knob 6 is Ee to move the cursbelaboy20bs page The small right knob is used to select individual characters for the highlighted cursor 8 of 15 Feb 25 2005 Symphony SECTION 9 SA160 SUPPLEMENT 2 4 4 PAGE SELECTION a Selection of any main page is performed using the large EY and small 3 rightknobs The large right knob 6 selects the page group NAV WPT orAUX The small right knob selects the desired page within a group To quickly select the default NAV page pressand hold GB 4 5 TO SELECT A DIRE
20. NORMAL PROCEDURES 7 of 15 PERFORMANCE 5 ec ook ee Re A 10 of 15 WEIGHT AND BALANCE 10 of 15 DESCRIPTION AND OPERATION 11 of 15 Feb 25 2005 1 of 15 SECTION 9 gt ymphony SUPPLEMENT 2 SA160 SECTION 1 GENERAL 1 1 INTRODUCTION The GNC 420 System is a fully integrated panel mounted instrument which contains a VHF Communications Transceiver and a Global Positioning System GPS Navigation computer The system consists of a GPS antenna GPS Receiver VHF COMM antenna and a VHF Communications Transceiver The primary function of the VHF Communication portion of the equipment is to facilitate communication with Air Traffic Control The primary function of the GPS portion of the system is to 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 s position velocity and time 1 2 SPECIFICATIONS Provided the GARMIN GNC 420 s GPS receiver is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications for a VFR IFR enroute terminal and non precision instrument approach GPS Loran C VOR VOR DME TACAN NDB NDB DME RNAV operation within the U S National Airspace System in accordance with AC20 138 b One of the approved sensors fora single or dual GNC 420 installation for Nort
21. gt ymphony GENERAL SA 160 AIRCRAFT VIEWS m ft 10 67 35 e je 2 11 6 92 LITI Ti EFEZIE a A O El 1 118 3 67 A g ES ZET L T1 W E I 3 27 10 75 0 86 2 82 Abb 1 1 1 Aircraft Views 1 2 Feb 25 2005 Symphony SECTION 1 SA 160 GENERAL 2 82 9 25 BEES F 1 72 6 67 6 960 22 84 Notes The ground clearance of the propeller at maximum takeoff weight and in the takeoff attitude is at least 0 180 m 7 in Maximum propeller diameter is 1 854 m 73in The wing area is 11 93 m 128 4 sq ft A minimum turning radius of 6 6 m 21 7 ft Pivot point to the wing tip can be achieved Control Surface Deflections Aileron Up 23 Down 17 Elevator Up 21 Down 20 Rudder Left 21 Right 21 Trim Tab Up 10 Down 20 Flaps Down 0 to 40 Abb 1 1 2 Aircraft Views Feb 25 2005 1 3 SECTION 1 gt ymphony GENERAL SA 160 1 1 INTRODUCTION This manual constitutes a Transport Canada approved Airplane Flight Manual for Canadian registered airplanes in accordance with AWM 523 In countries other than Canada Transport Canada operating rules may not apply Operators must ensure that the aircraft is operated in accordance with national operating rules Th
22. of the fuselage The amount of fresh air can be adjusted by pivot tabs inside the nozzles The heating system is used to supply heated air to the cabin and to the windshield Ram air flows through a shroud attached to the exhaust and a duct to the heat valve The heat valve is located on the firewall in the engine compartment Using this valve the amount of heated air can be regulated The valve is actuated by a control CABIN HEAT located on the center pedestal below the instrument panel viaa Bowden cable 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 knob is pulled out the heat relief valve opens Additional heat is available by pulling the knob out further Maximum heat is available with the cabin heat knob in the most rear position Via the heat valve the hot air travels through to the heated air distributor box This box is located in the cabin at the firewall By the heated air distributor the amount of heated air which should reach to the area of the pilot s and co pilot s feet and to the windshield can be adjusted A door inside the heated air distributor is operated by the control WINDSHIELD CABIN via a Bowden cable The control knob is located just below the CABIN HEAT control on the center pedestal For maximum effect the fresh air nozzles should be closed Feb 25 2005 7 47 SECTION 7 Symphon Y DESCR amp OPERATION S
23. 160 For maintenance and repairs the engine cowling consists of an upper and lower half fiberglass shell that can be removed In order to obtain maximum efficiency and time between overhauls the pilot should familiarize himself and follow the procedures recommended in the Lycoming Operator s Manual a Engine Controls Engine controls include a throttle a mixture control and a carburetor heat control The throttle mixture and carburetor heat controls are placed at the lower center of the instrument panel See Fig 7 2 The throttle controls engine power The throttle is fully open in the full forward position and closed in the fully aft position The throttle hasa friction lock Rotating the round knurled knob at the base of the throttle clockwise increases the friction and counterclockwise decreases the friction The fuel air ratio is adjusted by the mixture control The RICH position is full forward and full aft is the IDLE CUT OFF position For small adjustments the control may be moved forward by rotating the knob clockwise and aft by rotating the knob counterclockwise For larger adjustments the knob may be moved forward or aft by depressing the lock button in the end of control CAUTION GJ Do not force the pressure on the Mixture control and do not turn the knurled knob when the mixture control is already fully forward RICH as this may cause damage to the mixture control mechanism The c
24. 3 19 Feb 25 2005 4 30 Feb 25 2005 3 20 Feb 25 2005 4 31 Feb 25 2005 3 21 Feb 25 2005 4 32 Feb 25 2005 4 1 Feb 25 2005 5 1 Feb 25 2005 4 2 Feb 25 2005 5 2 Feb 25 2005 4 3 Feb 25 2005 5 3 Feb 25 2005 4 4 Feb 25 2005 5 4 Feb 25 2005 4 5 Feb 25 2005 5 5 Feb 25 2005 4 6 Feb 25 2005 5 6 Feb 25 2005 4 7 Feb 25 2005 5 7 Feb 25 2005 4 8 Feb 25 2005 5 8 Feb 25 2005 4 9 Feb 25 2005 5 9 Feb 25 2005 Feb 25 2005 Symphony AIRCRAFT SA 160 LOG OF EFFECTIVE PAGES PAGE DATE PAGE DATE 5 10 Feb 25 2005 7 4 Feb 25 2005 5 11 Feb 25 2005 7 5 Feb 25 2005 5 12 Feb 25 2005 7 6 Feb 25 2005 5 13 Feb 25 2005 7 7 Feb 25 2005 5 14 Feb 25 2005 7 8 Feb 25 2005 5 15 Feb 25 2005 7 9 Feb 25 2005 5 16 Feb 25 2005 7 10 Feb 25 2005 5 17 Feb 25 2005 7 11 Feb 25 2005 5 18 Feb 25 2005 7 12 Feb 25 2005 5 19 Feb 25 2005 7 13 Feb 25 2005 5 20 Feb 25 2005 7 14 Feb 25 2005 5 21 Feb 25 2005 7 15 Feb 25 2005 5 22 Feb 25 2005 7 16 Feb 25 2005 5 23 Feb 25 2005 7 17 Feb 25 2005 5 24 Feb 25 2005 7 18 Feb 25 2005 6 1 Feb 25 2005 7 19 Feb 25 2005 6 2 Feb 25 2005 7 20 Feb 25 2005 6 3 Feb 25 2005 7 21 Feb 25 2005 6 4 Feb 25 2005 7 22 Feb 25 2005 6 5 Feb 25 2005 7 23 Feb 25 2005 6 6 Feb 25 2005 7 24 Feb 25 2005 6 7 Feb 25 2005 7 25 Feb 25 2005 6 8 Feb 25 2005 7 26 Feb 25 2005 6 9 Feb 25 2005 7 27 Feb 25 2005 6 10 Feb 25 2005 7 28 Feb 25 2005 6 11 Feb 25 2005 7 29 Feb 25 2005 6 12 Feb 25 2005 7 30 Feb 25
25. 65 64 72 71 85 84 00 F ES 5 53 52 57 56 63 62 74 74 n po gt 51 50 55 54 61 60 71 71 NOTES 1 THEMAXIMUMALTITUDE LOSS DURING STALL RECOVERY CAN BE UP TO 250 FT 2 AT MIDDLE AND AFT C G POSITIONS LOWER ABOVE SHOWN VALUES BY 1 KT EXAMPLE WEIGHT 975 kg 2150 Ibs FLAPS 40 ANGLE OF BANK 30 STALL SPEED 55 KIAS 54 KCAS Figure 5 5 5 16 Feb 25 2005 Symphony AIRCRAFT SECTION 5 SA 160 PERFORMANCE TAKEOFF DISTANCE FOR SHORT FIELDS CONDITIONS FLAPS 20 LIFT OFF 58 KIAS TAKEOFF POWER SET BEFORE BRAKE RELEASE PAVED DRY RUNWAY ZERO WIND SPEED AT 50 ft 62KIAS WEIGHT 975 kg 2150 lbs ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C PRESS TOTAL TOTAL TOTAL TOTAL TOTAL ALT GROUND TO Ground TO crounp TO Grounp TO aRouNp TO ft ROLL CLEAR pont CLEAR ROLL CLEAR ROLL CLEAR ROLL CLEAR ft 50 FT ft 50 FT ft 50 FT ft 50 FT ft 50 FT OBS OBS OBS OBS OBS ft ft ft ft ft MSL 1050 1378 1148 1476 1230 1591 1329 1690 1411 1788 1000 1115 1444 1214 1558 1312 1657 1394 1772 1493 1886 2000 1198 1542 1296 1640 1394 1755 1493 1870 1575 1985 3000 1312 1673 1427 1804 1526 1919 1624 2034 1722 2149 4000 1460 1837 1558 1952 1673 2083 1772 2198 1870 2329 5000 1575 1985 1690 2116 1804 2231 1903 2362 2001 2477 6000 1706 2133 1821 2264 1936 2395 2051 2526 2149 2657 7000 1854 2297 1
26. ALT BAT switch and the ignition switch Rough Engine Operation gt Checklist 3 5 e Rough engine operation can be caused by various problems In the case of carburetor icing turn carburetor heat ON Wait for a decrease in engine roughness or an increase in RPM indicating ice removal If carburetor heat shows no effect and atmospheric conditions make carburetor icing unlikely if CAT indicator installed check reading after some minutes turn carburetor heat OFE Check the fuel valve isin ON position The auxiliary fuel pump supports the fuel supply to engine if the engine driven fuel pump does not work correctly Check the mixture control lever position adjust for maximum smoothness A unlocked primer may also cause for engine roughness Switching from BOTH to either L or R ignition switch position will identify a magneto ora spark plug problem Check the VM 1000 display for abnormal readings that may indicate the cause Precautionary Landing With Engine Power gt Checklist 3 5 f A precautionary landing with engine power usually offers sufficient time reserve to take all the necessary measures to minimize the danger The choice of the field should be made considering size surface conditions vegetation any obstructions in the planned 3 14 Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES approach direction and the current wind direction A fly over provides the opportunity for a better assessment of the sele
27. Eet EE 6 mm 1 4 in OPEN MEU a So E O AO E FULL RICH Propeller Area vinci in CLEAR Ignition Wi ode O Ay asd START TROI apena di O nre Eee AP O R O ADJUST to 1000 1200 RPM Oil pressure waz ainia CHECK NAV LT Switch at Night seeda itd dada ON e Engine Start With External Power Source External Powef SOULCE wss rro er rena CONNECT Start engine according b and c or b and d then TRT WE new yz IDLE External Power Plug aeree DISCONNECT OR e ADJUST to 1000 1200 RPM PIMC LOL aoi tit exe nl ee ra de da CHECK NOTE If engine does not start within 10 sec disengage the starter and try again after a few seconds f Warm Up Throttle sheep E 1000 1200 RPM AVIONIC Equipment ninio narran ON AS REQUIRED 4 10 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES VACUNA e Dc t n t ete AO CHECK HEIEREN CHECK Oil Temperature cete te ie e CHECK Circuit Breakers 4 eerte retener natans anta aene ono noo CHECK g Taxiing TA ATCA ccs eret iaa CLEAR enke APPLY SLOWLY LAA a A EEEE CHECK Control iii sc CHECK for free and correct movement h Ground Check A A NO APPLY Thiottle iia AA ACO Aa D X E RNA 1800 RPM Mastin CHECK T then R Maximum Drop 175 RPM Maximum Difference 50 RPM between magneto Ignition Within cnica timete BOTH Carburetor Heaton incoada ON RPM drop at least 50 RPM Torla IDLE Engine runs smooth with 500 700 RPM Carburetot Heat ssa tias
28. FUEL PUMPSwWitcli cett pret eno mere en OFF Feb 25 2005 4 15 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 PIT OU EAT Switch acia ci SRA nabo rca OFF LDGE Within aa Oaza on day OFF q Engine Shut Down Flaps 2ete enenatis RETRACT AVIONICS eat Zn O R O R Bn neret dieses OFF WMO tle inerti AR AO AD 1000 1200 RPM EE IDLE CUT OFF Ignition Switch aa feti ert e Ri OFF STROBEETSwitch entente al OFF NAV LT Switch at bei ie eet nett tete OFF DOME LT Switch at Night ttt tta ON INST LT MAP LT Dimmer Switch at Night OFF ALT BAT Switch on Day OFF ALI Switch at NIght 25 eter ettet ttt tette OFF r After Engine Shut Down All Electrical Equipient tirer tent tetra OFF Ignition SWI Ch a teret e ten ee remite OFF Throttle rre e terere pi pl eem FULL AFT MIXER eiii IDLE CUT OFF ContOlSIEK aid Rt z O eege LOCKED DOME LI Switch at Night A OFF BAT Switch atNight rta OFF Wheel Chocks nadania zd i eiim AA INPLACE Tie DOWNS ecards SECURE C VEMNES sie dE a dE EA A EE INSTALLED 4 16 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES 4 7 AMPLIFIED NORMAL PROCEDURES The following provides detailed information and supplementary notes for normaloperation ofthe aircraft a Preflight Inspection 4 5 a The aircraft should be given a thorough preflight check A check of the aircraft s logs is also required Scheduled aircraft inspe
29. Leading Edge with Vortex Generators CHECK Stall Warning System eror aeir CHECK Fuel Tank Vent Eine CHECK for free venting 4 6 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES Pitot TUBE wise aaa eine teres REMOVE pitot tube cover Pitot Tube Hole eiie rre rien e CHECK clear Fiiel TANK qe R O O O na CHECK VISUALLY for desired level Fuel Filler Cap tete ttti CHECK secure and vent unobstructed 3 Nose COWES aa acie iid ec aient diente id CHECK fasteners for security Windshield tetas CHECK for any damage ET CHECK for obstructions Landing Light zaa wii diia CHECK for condition Propeller and Spinner CHECK for nicks and cracks Generator Drive Belt edu CHECK tension A A AS CHECK level Oil Filler CUP iii CLOSE Oil Access DOOP srra A docenas CLOSE Nose Gear Strut and Wheel Fairing sss CHECK Nose Wheel Tire CHECK For proper inflation and general condition 4 Right Wing Wing Te CE aac nak AGI NAGIE FREE of ICE FROST SNOW Fuel Tank aiz id nod nai R R CHECK VISUALLY for desired level Fuel Hiller Cap coi dwa EGO By ege CHECK Secure and Vent unobstructed Wing Leading Edge with Vortex Generators 1 1111 CHECK Fuel Tank Vent Line CHECK for free venting Wing Tip and Lights reet CHECK Counter Weight CHECK for security of attachment Feb 25 2005 4 7 SECTION 4 gt ymphony N
30. Receiver Sensitivity Selection Button Q Pilot Intercom System ICS Volume Q Pilot ICS Voice Activated VOX Intercom Squelch mr Level ICS O Copilot ICS Volume Control O Copilot VOX Intercom Squelch Level cew Crew Isolation Intercom Mode Button mo Pilot Isolation Intercom Mode Button m Passenger Address PA Function Button n a Speaker Function Button Transceiver Audio Selector Buttons COM 1 COM 2 COM 3 Transmitter Audio Mic Selection Buttons COM NAV cou Split COM Button z Aircraft Radio Audio Selection Buttons NAV 1 NAV 2 z Feb 25 2005 DME ADF 9 of 11 SECTION 9 gt ymphony SUPPLEMENT 3 SA160 Annunciator Test Button Locking Screw Access O Photocel Automatic Annunciator Dimming 7 4 ICS MODES a PILOT mode isolates the pilot from everyone else and dedicates the aircraft radios to the pilot exclusively The copilot and passengers share communication between themselves but cannot communicate with the pilot or hear the aircraft radios b CREW mode places the pilot and copilot on a common ICS communication channel c ALL mode allows full intercom communication between everyone plugged in to the GMA 340 Aircraft radios are heard by all d MUSIC 1 and MUSIC 2 stereo entertainment inputs are affected by the intercom mode selected 7 5 MARKER BEACON RECEIVER The marker beacon audio level is aligned at the factory to produce its rated audio output However the o
31. Spin Recovery Procedure 3 5 q etes 3 20 3 1 GENERAL This section contains the recommended procedures for coping with various emergencies or critical situations as required by the Aviation Authorities as well as those necessary for operation of the aircraft as determined by the operating and design features of the aircraft Emergency procedures associated with optional systems and equipment which require handbook supplements are presented in Section 9 Supplements This section is divided into two main parts 1 2 3 2 The first part contains the emergency procedure checklists These checklists are clearly arranged to give an action sequence to be followed during given situations without explanations The second part provides amplified emergency procedures corresponding to the emergency procedures checklist items These amplified emergency procedures contain additional information to Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES provide the pilot with a more complete description of the procedures and a better understanding of the reasons for the actions listed The numbers located in parentheses after each paragraph heading indicate the corresponding checklist paragraph It is recommended that pilots familiarize themselves with the emergency procedures described in this section and review them periodically This process helps ensure pilots take the appropriate action should an eme
32. With sufficient altitude and after selection of a suitable field a spiral pattern should be attempted around the selected field In this way a series of correction possibilities are available in order to complete a precise landing at the chosen point without engine power While descending if radio contact is available notify the corresponding ground station of your difficulty location and intentions Excess altitude may be lost by widening the pattern using flaps side slipping or a combination of these WARNING _ f Atno time should the airspeed reduce below the stalling speed for the configuration setting Note This speed increases by increasing the angle of bank of the aircraft See section 5 Fig 5 4 Stalling Speed In order to contact the ground at the lowest possible speed flaps should be full extended just before landing and the speed should be 65 KIAS Feb 25 2005 3 13 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 While perform a forced landing on unknown field damage possible collision with obstacles and even overturning cannot be excluded Seat belts and harnesses must be tight to reduce the possibility of injury In order to reduce the danger of a short circuit and or fire the fuel supply to the engine should cut off and the electrical system turned off Cut off the fuel supply by moving the Mixture control to the position IDLE CUT OFF and the fuel valve to OFE Turn off the
33. a rudder with aerodynamic and mass compensation at the top end The rudder is connected to the vertical stabilizer by three hinged brackets The lower one has a yoke that drives the rudder by means of control cables The horizontal tail has a stabilizer and an elevator The elevator is attached to the stabilizer by piano type hinges and is driven by a pushrod at the center of the elevator base The elevator has a trim tab which is attached to the trailing edge starboard side The elevator is aerodynamic and mass balanced at the tips 7 7 FLIGHT CONTROLS The aircraft is equipped with dual controls The ailerons and the elevator are operated by the control stick and the rudder by foot pedals in front of each seat via a system of control cables pulleys and turnbuckles See Fig 7 1 7 2 and 7 3 The trim tab serves the dual function of providing trim control and pitch control forces The trim tab is actuated by a trim control wheel located on the control console between the seats Forward rotation of the wheel gives nose down trim and aft rotation gives nose up trim Feb 25 2005 7 7 SECTION 7 gt ymphony DESCR amp OPERATION S 160 AILERON CONTROL SYSTEM Figure 7 1 Aileron Control System 7 8 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION ELEVATOR CONTROL SYSTEM Figure 7 2 Elevator Control System Feb 25 2005 7 9 SECTION 7 gt ymphony DESCR amp OPERATION SA 160 RU
34. and freedom of operation there The static dischargers should be firmly attached and in good condition The baggage in the baggage compartment should be securely anchored down Close the baggage door and lock it by means of both locks 4 20 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES Next through the fuel system low point drain located on the bottom of the cabin drain fuel into clear cup and check for water and sediment Drain until water or sedimentis gone Check the pitot and static systems low point drains for water Finally enter the cabin and turn ON the BAT switch Retract the flaps and switch BAT OFE b Before Starting Engine 4 5 b Prior to starting the engine a pre flight check must be Icompleted At night use the dome light The fuel on board must be sufficient for the flight Pilot and passenger must be securely fastened by the seat lap belts and shoulder harnesses and the doors must be closed and secure NOTE Make sure that with the seat belts securely fastened all controls can be easily reached and can be move full travel without obstruction Check all navigation material necessary for the flight is on board at night additionally a flashlight for emergency purposes The AVIONICS switch should be in OFF position CAUTION fy Any Avionics in the ON position could be damaged during engine start NOTE Equipment unnecessarily switched ON during the start sequence co
35. are four additional features that the fuel computer provides REM Fuel remaining onboard BRN Fuel burned since last power up HRS Hours of fuel remaining ADD Add fuel to computer memory An exclusive feature of our fuel flow computer is its ability to damp out the wide variations in displayed fuel flow 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 Fuel Remaining Alert Your fuel computer has a built in Low Fuel Remaining warning annunciator When the computed fuel total is less than a factory programmed amount 10 gallons standard the display will flash 4 6 INITIAL SET UP OF THE FUEL COMPUTER The initial fuel system set up is performed at the aircraft factory In the event that a system re initialisation would be required refer to the VM 1000 installation manual provided with your aircraft for the proper procedures 8 of 27 Feb 25 2005 Symphony SA160 4 7 ADDING FUEL TO THE FUEL COMPUTER WARNING GJ IMPROPER USE OF THIS FEATURE WILL GIVE YOU INCORRECT FUEL REM AND HRS INFORMATION INSURE THAT YOU UNDERSTAND THE OPERATION OF THIS SYSTEM BEFORE USING IT INFLIGHT AFTER INSTALLATION AND PERIODICALLY THEREAFTER VERIFY THAT THE SYSTEMS ACCURACY IS ACCEPTABLE FOR YOUR INTENDED USE Your fuel computer has a unique feature that allows you to ADD fuel acco
36. effectiveness 4 15 CHRONOMETER SYSTEM OPERATION opt The chronometer system has BOTH digital and graphic displays of various time related parameters The digital readout displays hours HRS minutes MIN and seconds SEC continuously The exclusive positive action rotary 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 watch timer will both count up and count down In the Count Down mode the graphic display initially starts at full scale and as time counts down decreases in size proportionately i e when half the initial time remains half of the graph remains This is very handy for timing instrument approaches fuel tank changes and next fix arrival An additional feature is the alarm annunciator When time expires the entire display flashes alerting you to this fact This is great for applications suchas timing approaches time to destination or expected checkpoint or time to change tanks to name just a few 20 of 27 Feb 25 2005 Symphony SA160 The following page contains easy steps for initial setup and operation of your chronometer 4 16 INITIAL CHRONOMETER SET UP You will want to set your chronometer s universal and locall time functions This is easily done by performing the following steps SETTING UNIVERSAL TIME COORDINATED UTC STEP 1 With power on place
37. engine oil cooling system performance For new engine installations you can take advantage of the high accuracy and repeatability for analyzing the engine oil cooler system efficiency If the cooling does not seem to be effective enough you can make changes and repeat your tests with the confidence that the next test data will reflect the results of your changes Oil Temperature Alert Your oil temp system also provides you with built in warning annunciators If the oil temperature rises above redline the system captures the event and the display is flashed until the problem is corrected This is a realadvantage in the busy cockpit 4 5 FUEL COMPUTER SYSTEM OPERATION Fuel Pressure Fuel Pressure is displayed both digitally and graphically As fuel pressure rises the graph rises proportionately Full color operating range marks are provided that indicates the normal operating range of fuel pressure for your engine at a glance The digital display allows you to see small variations and make notations of typical fuel pressure behaviour Fuel Pressure Alert The system has a built in warning system and will flash should fuel pressure move outside of the limits for your particular engine Fuel Flow Feb 25 2005 7 of 27 Symphony IRCRAFT SA160 Fuel Flow is displayed both digitally and graphically As fuel flow increases the graph increases proportionately The digital display provides tenth gallon resolution There
38. however the maximum baggage compartment floor load for each baggage area red marking is limited to a maximum of 99 lbs 45 kg WARNING Do not place any small loose articles in the baggage compartment All baggage must be stowed in containers such as packs suitcases or bags to avoid potential injuries in the event of a forced landing 7 21 SEATS AND SEAT BELTS The aircraft cabin provides side by side seating for two The seats are adjustable fore and aft To position the seat lift the handle located below the seat frame slide the seat into position and release the handle Ensure that the seat is locked into position The seats are equipped with automatic four point seat belts shoulder harness assemblies To fasten the seat belts shoulder harness a center link is used The design incorporates an inertia reel system for the shoulder portion The shoulder harnesses are attached to the cage truss structure behind the seats and allows for complete freedom of movement of the upper torso area In the event of asudden deceleration the reels lock up to provide positive restraint for the user 7 16 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 7 23 DOORS AND WINDOWS The SA 160 has two cabin doors Each door is secured by a three point latch system actuated by an interior and exterior door handle on each cabin door To close the door from inside the airplane pull the door shut and push the door locking
39. is incorporated into the SA 160 The set consists of the antenna which is mounted at the bottom of the fuselage the encoder located behind the instrument panel and the receiver transmitter unit which is mounted in the instrument panel just below the NAV COM radio The circuit breaker for the transponder is labeled ATC Fig 7 XX shows the Transponder front view For operating instructions and further information about the VHF NAV COM radio and the transponder please refer to the appropriate Bendix King publications Feb 25 2005 7 53 SECTION 7 Symphony DESCR amp OPERATION SA 160 0000 O 00000000 O er ae POWER LED Co Pilot y SQUELCH VOLUME Volume Squelch Volume Squelch Pilot MODE SWITCH ONLY LEFT BOTH COMM FREQUENCY NAV INFORMATION NAV FREQUENCY WINDOW WINDOW H E 7 m WINDOW j BENDIX KING KX 125 TS0 ops 3 5c D FLAG NAV MODE BUTTON COMM FREQUENCY TRANSFER BUTTON COMM FREQUENCY COMM VOLUME PULL TEST KNOB SELECTION KNOBS STANDBY FREQUENCY Figure 7 18 INTERCOM Control Panel and NAV COM Receiver Transmitter 7 54 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 00000 000000 00000 000000 O O 00000 00000 00000000 O REPLAY LIGHT CODE WINDOWS KT 76A TSO B
40. it may be advisable to make a off field landing while power is still available particularly if other indications of actual oil pressure loss such as sudden increase in temperatures or oil smoke or oil on the windshield are apparent and an airfield is not close If an engine stoppage occurs proceed with Landing Without Engine Power Checklist 3 5 d Feb 25 2005 3 17 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 Power Supply System Malfunction gt Checklist 3 5 Loss of alternator output can be detected by monitoring the ammeter and the voltmeter on the VM 1000 indicator Verify the ALT switch is on Check the ALT FLD circuit breaker and reset if required Attempt to reset the over voltage protection system of the alternator regulator by turning ALT OFF and then ON Check the ammeter and voltmeter If the alternator will not reset turn OFF the ALT switch and reduce the electrical load to a minimum All electrical load is now being supplied by the battery Turn off all non essential electrical equipment Proceed toward nearest airfield NOTE A power supply malfunction has no effect of the engine operation Excessive Rate Of Charge Checklist 3 5 m With a faulty alternator regulator an excessive rate of charge and an overcharging of the battery may occur Electrical equipment may be damaged by over voltage If ammeter and voltmeter on the VM 1000 indicator indicates an excessive rate of char
41. performed at the factory In the event that a system re initialisation would be required refer to the VM 1000 installation manual provided with your aircraft for the proper procedures Feb 25 2005 3 of 27 Symphony IRCRAFT SA160 SECTION 4 NORMAL PROCEDURES OPERATION 4 2 TACHOMETER OPERATION The tachometer system provides both a full sweep graphic analog display and four place digital displays When you start the engine you will see the analog graph rise in proportion to the engine speed Fullcolor range marks provide you with a quick reference to monitor normal caution and red line engine RPM RPM The digital readout provides you with exact RPM information The resolution orincremental steps of the digital display is 10 RPM For example the display might read 2400 and after you make a slight increase in power 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 to the pilot We recommend using the digital display for RPM checks and letting the engine stabilize for a minimum of three seconds during the checks The high accuracy of the tach will allow you to follow long term performance trends of your engine and prop such as static maximum rpm carb heat effectiveness and typical mag drops These can be important indicators of engine and accessory condition Engine Operating Hours An
42. power as required and select carburetor heat OFE NOTE In order to avoid an overcooling of the engine avoid prolonged descent at high speed and low power WARNING _ GJ 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 minutes duration Before continuing descent perform a 3 minute level flight with flapsup refer section 7 Feb 25 2005 4 29 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 n Before Landing 4 5n Check that seat belts are fastened securely The mixture control should be kept FULL RICH to ensure maximum acceleration if it should be necessary Turn ON the auxiliary fuel pump the carburetor heat and the landing light Extend the flaps as required On final approach landing flaps should be selected according to the runway surface wind conditions and aircraft loading Adjust trim Verify the parking brake control knob is pushed in CAUTION If landing is made with the parking brake set the brakes will maintain any pressure applied after touchdown The final approach speed with flaps extended to 40 is 65 KIAS NOTE It is recommended that all necessary landing checks and actions in the cabin are completed before turning into the final approach In this way the pilot s attention can be dedicated to controlling
43. precise for most flight planning purposes Temperature correction is explained on the Performance Note Fuel Required for Climb 6 4 Liters 1 69 U S Gal Climb Distance 12 6 NM The cruise distance is now Total Distance 280 Climb Distance 13 Cruise Distance 267 NM Feb 25 2005 5 5 SECTION 5 gt ymphony PERFORMANCE SA 160 With an assumed headwind of 20 kts enroute the ground speed for cruise is 117 20 97 kts Using these two values the time for the cruise can be calculated 267 NM 97 kt 2 8 h The fuel required for cruise is 2 8 h x 28 l h 7 AU S Gal h 78 4 1 20 7 U S Gal 45 minute reserve 45 60 x 28 1 h 7 4 U S Gal h 21 1 5 54 U S Gal Nextthe total fuel required can be calculated as follows Engine start taxi and takeoff 4 0 1 1 05 U S Gal Climb 6 4 1 1 69 U S Gal Cruise 78 4 1 20 7 U S Gal Reserve 21 0 1 5 54U S Gal Total fuel required 109 8 1 29 U S Gal d Landing For estimating the landing distance at the destination airfield a procedure similar to takeoff should be used For this fig 5 12 Landing Distance for short fields is to be used The 5 6 Feb 25 2005 Symphon Y SECTION 5 SA 160 PERFORMANCE values are based on using the normal procedure Landing Short Field see Section 4 NORMAL PROCEDURES By means of the corresponding column with the air temperature and the line with corresponding altitude the landing distances a
44. proceed toward the nearest airfield and wait for better weather conditions With an ice accumulation on the wing leading edges of 5mm or more performa landing with flaps up orin 20 position The landing approach speed should be higher depending upon amountofthe accumulation Feb 25 2005 3 19 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 Static Source Blockage IFR Checklist 3 5 If erroneous readings of the static source instruments aispeed altimeter and vertical speed are suspected the alternate static source valve on the left side of instrument panel should be opened to supply static pressure from the cabin to these instruments With the alternate static source on adjust indicated airspeed slightly during climb or approach according to the Airspeed Calibration Alternate Static Source table in section 5 as page 5 11 appropriate for vent configuration causing the aircraft to be flown within the normal operating speed limits Spin Recovery Procedure Y Checklist 3 5 p WARNING Intentional spins in the SA 160 are prohibited Cause of inadvertent spins is usually the result of heavy or insensitive controlinputs The spin recovery is unproblematic with the SA 160 Once the spin is recognized first move the throttle to idle and the ailerons to neutral Stop the rotation of the aircraft by applying the rudder full opposite to the direction of yaw At the same time move the control stick forward up until the e
45. removed before flight 7 48 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION Air Speed Indicator l l l ESS a a Altimeter Vertical Speed Indicator To Transponder Blind Encoder IFR l l l L from inside of cabin I I I I I I Alternate Static Source gt Valve I I I I I I Static Port 1 mmm mmm NA pm mmm pm mmm Em w jm mm mmm mmm JL r Static Pressure Pitot Pressure A 0 SCH Drain Valves Static Port 2 Figure 7 16 Static and Pitot Pressure System Schematic Feb 25 2005 7 49 SECTION 7 gt ymphony DESCR amp OPERATION SA 160 Alternate Static Source IFR An alternate static pressure source valve is installed on the left instrument panel This valve supplies static pressure from inside the cabin instead of the external static ports If a blockage in the standard static system is suspected due water or ice the alternate static source valve should be turned on Whenever the alternate static pressure source is selected refer to airspeed calibration table Alternate Static Source in Section 5 for the corrections to be applied 7 41 VACUUM SYSTEM The vacuum system is provided to operate the air driven directional and attitude gyro instruments The systems consists of an engine driven vacuum pump a vacuum relief valve filters a vacuum
46. smoke or expose a flame within 100 feet of the cleaning area Feb 25 2005 8 14 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 1 Remove Cowling WARNING Do not use gasoline or other highly flammable substances Do not attempt to wash an engine when it is still hot or running CAUTION Do not direct cleaning solvents or water streams at openings on the alternator vacuum pump starter or magnetos 2 Carefully cover the openings on the alternator the vacuum pump the starter and on the magnetos 3 If engine is contaminated with salt or corrosive chemicals first flush engine compartment with water 4 Apply a suitable solvent or cleaning agent to the engine compartmentin accordance with manufacturer s instructions 5 Allow the solvent to remain on the engine from five to ten minutes CAUTION _ GJ Cleaning agents should never be left in engine compartment Remains of cleaner or solvent may cause damage to components such as neoprene seals and silicone fire sleeves 6 Thoroughly rinse with clean warm water 7 Allow engine to dry or dry it completely using compressed air 8 Remove all coverings positioned to protection while cleaning 9 Lubricate all control arms and moving parts as required 10 Reinstall cowling 8 15 Feb 25 2005 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE WARNIN
47. sparingly If the carpet is soiled use a commercially available carpet cleaning product 8 14 DURING FLYABLE STORAGE The following guidelines are applicable for situations in which the aircraft is not used for periods of time between 7 and 30 Days They are meant to help prevent deterioration of the aircraft during periods of non use NOTE 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 engine for storage check for correct oil level and add oilif necessary to bring the level to the full mark Then run the engine for at least five minutes at 1200 to 1500 RPM with oil and cylinder heat temperatures in the normal operating range Shut down the engine Top up the fuel tanks to prevent condensation of water in the tanks If a dry hangar is not available secure the aircraft as described above in this section paragraph 8 9 c De Down Install covers over the cabin area to keep out moisture and sunlight Install the pitot tube cover To prevent oxidation of the finish the use of light colored slip covers over the composite fuselage during extended periods of outdoor tie down especially in summer time is recommended 8 17 Feb 25 2005 Symphony SECTION 8 AIRCRAFT SA 160 GROUND HANDLING SERVICING amp MAINTENANCE After every seven days during storage rotate the propeller by ha
48. suction gauge and the necessary connecting tubing See Fig 7 17 The dry type air vacuum pump is flanged on the upper rear engine accessory case A shear drive protects the pump from damage If the vacuum pump fails or the drive shears the air driven directional and attitude gyros will become inoperative Avacuum gauge placed on the upper leftinstrument panel provides the pilot with the system vacuum pressure during operation A prolonged pressure decrease in the system 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 gauge or a collapsed line In the event of any gauge variation from the normal the system should be checked by an authorized mechanic to prevent possible damage to system components 7 50 Feb 25 2005 gt ymphony SECTION 7 AIRCRAFT SA 160 DESCR amp OPERATION ATTITUDE GYRO e GAUGE Be vs Pee mm rm e Y DIRECTIONAL gt cu GYRO ke m E VACUUM SYSTEM AIR FILTER ENGINE DRIVEN VACUUM PUMP ui VACUUM RELIEF VALVE VACUUM mm pm mm mm mm mm mm mi INLET AIR Figure 7 17 Vacuum System Feb 25 2005 7 51 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 or eventual syste
49. the EC 100 is performed at the aircraft factory In the event that a system re initialisation would be required refer to the VM 1000 installation manual provided with your aircraft for the proper procedures 4 19 EC100 SYSTEM OPERATION The EC100 system provides several categories of easily accessed information Select the desired category by pressing the W button to go 24 of 27 Feb 25 2005 Symphony SA160 forward or the 4 button to go backwards When you see a category you want press the T button to select it and again to see further information The following lists the major categories that may be selected 1 ENGINE INFORMATION Some of the typical subjects are POWER CYLNDRS F COMP etc 2 AIRCRAFT OPERATIONAL CHECKLISTS Some typical subjects are CLDSTRT HOTSTRT RUNUP TAKEOFF etc NOTE You may customize your checklist on paper then send it to the factory and we will program a permanent memory chip We recommend sending this in along with your fuel calibration info See sheets in Tllustrations section for both fuel cal and checklist recording 3 ALERTS and WARNINGS These are conditions are of importance and corrective action and or attention is needed When an alert warning condition initially happens the EC100 will automatically begin to flash the condition and a pulsing audio side tone will be momentarily present Each time any button is pressed the EC100 alarm will be removed for appro
50. the aircraft CAUTION GJ The maximum speed with flaps in extended position is 90 KIAS 4 30 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES o Landing 4 50 Normal Conditions The amount of flap used during approach and landing should be varied according to the runway surface wind conditions and aircraft loading It is recommended generally to perform the touch down at the minimum possible safe speed consistent with existing conditions Under normal conditions that will be with full extended flaps and approach speed of 65 KIAS When landing in a strong wind particular in crosswind it can be required to select a higher approach speed and extend the flaps only partially or not at all When landing flare the aircraft so that it flares out at approx 0 5 m over and parallelto the runway surface While decreasing speed increase angle of attack by easing the stick back so that the aircraft contacts with the lowest possible speed main wheels firstat the lowest possible speed After touch down hold the nose wheel off the ground as long as possible and as the aircraft slows down gently lower the nose Apply brakes as required Balked Landing After making the decision for a balked landing move the throttle full forward swiftly but not abruptly and turn OFF the carburetor heat to ensure the maximum engine power An easy torque effect of the aircraft around the longitudinal axis to the Whilst accel
51. the pilot s headset and microphone directly to COM 1 in case the power is interrupted or the GMA 340 unit is turned off SECTION 4 NORMAL PROCEDURES Normal operating procedures are completely described in the GARMIN GMA 340 Audio Panel Pilot s Guide P N 190 00149 10 Rev A or later appropriate revision NOTE The GMA 340 Audio Panelis shown in figure 7 1 4 1 POWERING ON THE GMA 340 To turn the unit on rotate the left small knob Q clockwise past the click 4 of 11 Feb 25 2005 Symphon d SECTION 9 SA160 SUPPLEMENT 3 4 2 SELECT A TRANSCEIVER COMx Press either COM 1 MIC COM 2 MIC or COM 3 MIC button for selection of either COM 1 COM 2 or COM 3 for both MIC and audio source The active com audio is always heard on the headphones Additionally each audio source can be selected independently by pressing COM 1 COM 2 or COM 3 When selected in this way they remain active as audio sources regardless of which transceiver has been selected for microphone use 4 3 SELECT THE INTERCOM MODE To activate other then ALL mode press or button Press again to deactivate the mode The operator can switch directly from PILOT to CREW or from CREW to PILOT by pressing the other mode button The ALL modeis active when neither PILOT nor CREW LED arelit 4 4 ADJUSTING INTERCOM VOLUME AND SOUELCH a LEFT SMALL KNOB O Unit ON OFF power control and pilot ICS volume Full counterclockwise detent position is OFF
52. the selector switch in the straight up position between the RUN and STOP positions The display should go blank STEP 2 Turn the power off for a few seconds then back on After a short period of time the display will alternate between UTC or LOCH STEP 3 First you 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 value a few ahead of actual time to allow you to set seconds Move the selector to SEC and set it to your desired future time Move the switch to the STOP position STEP 4 When the preset time equals the current time move the selector switch to the straight up position as before The display will read UTCrdy Wait for this message to disappear then move the selector to any desired position You can now check UTC for Feb 25 2005 21 of 27 Symphony IRCRAFT SA160 the correct universal time SETTING LOCAL TIME STEP 1 With power on place the selector switch in the straight up position between the RUN and STOP positions The display should go blank STEP 2 Turn the power off for a few seconds then back on The display will now alternately show UTC and LOC STEP 3 When the display shows LOC move the selector switch to the HRS position When the hours value gets to the correct hour move the switch to
53. tone The large left knob is used to tune the megahertz MHz value of the standby frequency for the COM transceiver or the VLOC receiver whichever is currently selected by the tuning cursor The small left knob is used to tune the kilohertz kHz value of the standby frequency for the COM transceiver or the VLOC receiver whichever is currently selected by the tuning cursor Press this knob momentarily to toggle the tuning cursor between the COM and VLOC windows Feb 25 2005 13 of 16 SECTION 9 ymphony SUPPLEMENT 1 SA160 The COM flip flop key is used to swap the active and standby COM frequencies Press and hold to select emergency channel 121 500 MHz The VLOC flip flop key al is used to swap the active and standby VLOC frequencies i e make the selected standby frequency active 2 Right hand Keys and Knobs Therange key allows selecting the desired map scale Use the up arrow side of the key to zoom out or the down arrow side to zoom in The direct to key allows entering a destination waypoint and establishing a direct course to the selected destination The menu key ED displays a context sensitive options list The options list allows making settings changes which relate to the currently displayed page The clear key is used to erase information or cancel an entry Press and hold this key to immediately display the Default NAV Page Theenterkey EB is used to approve an operation or complete data entry
54. using that navigation aid and the required navigation aid must be operational e VANV information may be utilized for advisory information only Use of VNAV information for Instrument Approach procedures does not guarantee Step Down Fix altitude protection or arrival at approach minimums in normal position to land 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 operation refer to Pilot s Guide for procedure id necessary a dis spd nm kts sets navigation units to nautical miles and knots b alt Vv ft fpm sets altitude units to feet and feet per minute c map datum WGS 84 sets map datum to WGS 84 see note below d posn deg min sets navigation grid units to decimal minutes Note In some areas outside in United States datums other than WGS 84 or NAD 83 may be used If the GNS 430 is authorized for use by the appropriate Airworhiness authority the required geodetic datum must be set in the GNS 430 prior to its use for navigation Feb 25 2005 5 of 16 SECTION 9 gt ymphony SUPPLEMENT 1 SA160 SECTION 3 EMERGENCY PROCEDURES 3 1 ABNORMAL PROCEDURES a Missing or Invalid Navigation Information If GARMIN GNS 430 navigation information is not available or invalid utilize remaining operational navigation equipment as required b RAIM POSITION WARNING If that message is displayed the syst
55. weight approved for ground maneuvre It includes weight of start taxi and run up fuel Maximum Takeoff Weight Maximum weight approved for the start of the takeoff run Maximum Landing Weight Maximum weight approved for the landingtouchdown Maximum Zero Fuel Weight Maximum weight exclusive of usable fuel g Other Definitions WARNING le Methods procedures or limits which must be followed precisely to avoid injury or death CAUTION Methods procedures or limits which must be followed to avoid damage to equipment NOTE Additional procedures or information pertaining to the text 1 14 Feb 25 2005 Symphon Y SECTION 2 SA 160 LIMITATIONS SECTION 2 LIMITATIONS TABLE OF CONTENTS 2 1 A 2 2 2 3 Atfspeed Limitations ao ir a Ant 2 2 2 Airspeed Indicator Markings risieda oa 2 3 27 Power Plant Limitations ettet eres 2 4 29 Engine Parameter Color Marking esse 2 5 2 11 Weight Limits c ertet ra t cnet 2 6 2 13 Center Of Gravity Ee UE 2 6 2 15 Maneuver LIMIS seinerseits ae ni sainan oL irr neas 2 6 2 17 Flight Load Factor Limits eene 2 7 PND TOW P PA 2 7 2 21 Kinds of Operations enata ettet eritis 2 7 2 23 Fuel Limitations resesi ptt hr t neni eiie 2 8 225 Other Ben E e 2 8 a Airframes ibid 2 8 2 27 Temperature Limitation ssion ieaie 2 8 2 29 Placards 5 ente
56. 0 6000 74 685 655 625 600 570 8000 73 590 560 535 510 485 10000 73 485 460 430 410 385 12000 73 380 355 330 310 285 14000 73 270 250 225 205 185 NOTE LEAN MIXTURE AS PER LYCOMING O 320 INSTRUCTIONS AT 5000 FT AND ABOVE EXAMPLE E WEIGHT 1990 Ibs RATES FOR GIVEN WEIGHTS THE PRESSUREALTITUDE MSL CORRESPONDING PERCENTAGE IS AIR TEMPERATURE 15 C TO BE CONSIDERED THE EXAMPLE WEIGHT IS 50 OF THE CLIMB SPEED 80 KIAS DIFFERENCE BETWEEN 1830 LBS AND 2150 RATE OF CLIMB 838 ft min LBS BETWEEN THE READ VALUES OF CLIMB Pd Figure 5 7 Feb 25 2005 Symphon Y SECTION 5 SA 160 PERFORMANCE TIME FUEL AND DISTANCE TO CLIMB CONDITIONS WEIGHT 975 KG 2150 LBS FUEL MIXTURE AS RECOMENDED BY LYCOMING FLAPS 0 O 320 LEANING SCHEDULE FULL THROTTLE ZERO WIND ISA FROM SEE LEVEL fp SC TIME FUEL USED DISTANCE i US NM ft SR a 1 GAL 1000 79 1 5 1 0 0 26 1 9 2000 78 3 0 2 2 0 58 4 0 3000 77 4 7 3 4 0 90 6 3 4000 76 6 6 4 6 1 21 8 7 5000 75 8 6 6 0 1 58 11 5 6000 74 10 9 7 4 1 95 14 5 7000 73 13 3 8 9 2 35 17 8 8000 73 16 1 10 6 2 80 21 5 9000 73 19 3 12 4 3 28 25 9 10000 73 23 2 14 5 3 83 31 0 11000 73 27 8 17 0 4 49 37 8 12000 73 33 7 20 0 5 28 46 6 NOTE 1 ADD 4 0 1 APPROX ONE GALLON OF FUEL FOR START TAXI AND TAKEOFF 2 FOR TEMPERATURES ABOVE STANDARD INCREASE VALUES BY 10 FOR EVERY 10 C EXAMPLE Dw DEP AIRFIELD PRESSURE ALTITUDE 2000 ft TIME 109 min 3 min 79 min DEP AIRFIELD TEM
57. 05 Date of Issue Feb 25 2005 DATE 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 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 PAGE 16 of 27 17 of 27 18 of 27 19 of 27 20 of 27 21 of 27 22 of 27 23 of 27 24 of 27 25 of 27 26 of 27 27 of 27 DATE 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 Symphony SECTION 9 IRCRAFT SUPPLEMENT 6 SA160 LIST OF REVISIONS Rev Page WE Na Date No Description ii Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 6 SUPPLEMENT 6 TABLE OF CONTENTS SECTION PAGE GENERAL ae E EEN en EN 2 of 27 LIMITATIONS 04 ek e ym y Ree de UR m 3 of 27 EMERGENCY PROCEDURES 3 of 27 NORMAL PROCEDURES 3 of 27 PERFORMANCE oroa uum ERR EET 3 of 27 WEIGHT AND BALANCE 4 of 27 DESCRIPTION AND OPERATION 4 of 27 Feb 25 2005 1 of 27 SECTION 9 gt ymphony SUPPLEMENT 6 SA160 SECTION 1 GENERAL 1 1 INTRODUCTION The VM 1000 Electronic Powerplant Instrumentation system is a multi channels engine monitoring system that provides the pilot with all the necessary engine parameters fuel indication and flight parameters to enable safe operation and management of the powerp
58. 12000 2700 2600 59 4 123 26 6 9 2500 53 8 118 24 6 3 2400 50 0 114 22 5 8 2300 44 4 107 19 5 0 2100 40 6 101 18 4 8 2000 34 4 88 15 4 0 EXAMPLE WEIGHT 975 kg 2150 Ibs TEMPERATURE 7 C PRESSURE ALTITUDE 4000 ft ENGINE SPEED 2400 RPM BHP 65 TRUE SPEED 114 KTAS MIN FUEL CONSUMPTION 29 Vh 7 7 U S Gal h Figure 5 9 2 Feb 25 2005 5 21 SECTION 5 gt ymphony PERFORMANCE SA 160 BEST RANGE PROFILE CONDITIONS ZERO WIND ISA WEIGHT 975 kg 2150 lbs INITIAL FUEL LEAN MIXTURE UP TO 75 POWER FOR BEST LOADING 110 LITERS 29 1 U S GAL USABLE ECONOMY AND ADJUST RICH ABOVE75 12 000 10 000 AZ m o w 8000 AS UL RS i lt LLI a S 6000 5 lt LLI e 5 o HI 4000 e D a Bl 2000 d PS E ax EN x S R 4 200 250 300 350 400 450 RANGE NM NOTE RANGE INCLUDES START TAXI CLIMB AND DESCENT WITH 45 MINUTES RESERVE FUEL AT MAXIMUM RANGE POWER Figure 5 10 5 22 Feb 25 2005 Symphony ZONY SECTION 5 SA 160 PERFORMANCE ENDURANCE PROFILE
59. 165 lbs but in the front or rear area maximum 45 kg 99 Ibs Typical Aircraft Weights a Empty Weight depending on installed equipment 630 660 kg 1389 1455 Ibs b Maximum Useful Load 345 kg 761 lbs 1 6 Feb 25 2005 Symphony SECTION 1 SA 160 GENERAL Cabin and Entry Dimensions a Maximum Cabin Width 1 10 m 43 3 in b Maximum Cabin Length 1 22 m 48 0 in c Maximum Cabin Height 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 Baggage Spaces a Compartment Width 0 44 m 17 3 in 0 87 m 34 3 in b Compartment Length 1 255 m 49 4 in c Compartment Height 0 45 m 17 7 in 0 77 m 30 3 in a Volume 870 1 30 72 cu ft Specific Loadings a Wing Area Loading 81 7 kg m 16 73 Ibs sq ft b Power Loading Takeoff Power N 975 x 9 81 N 0 122 8 19 kg kW 13 89 Ibs hp Feb 25 2005 1 7 SECTION 1 Sy mphony GENERAL SA 160 1 5 SYMBOLS ABBREVIATIONS AND TERMINOLOGY The following definitions are for symbols abbreviation and terms which are used in this handbook or are relevant for the pilot during the operation of the Aircraft a General Airspeed Terminology and Symbols CAS Calibrated Airspeed means the indicated speed of an aircraft corrected for position and instrument error CAS is equal to TAS in standard atmosphere at sea level KCAS Calibrated Airspeed expressed in
60. 37 Mixture Control 38 Fuel Level Indicator 39 OAT CAT Indicator optional 40 Circuit Breakers 41 Flap Switch 42 Dimmer Switch for Instrument Lights 43 Dimmer Switch for Map Lights 44 Heated Air Distributor Control 45 Headset Jacks 46 Cabin Heat Control 47 FuelShut Off Valve 48 Primer Pump optional 49 Parking Brake optional Figure 7 4 Instrument Panel Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION INTENTIONALLY LEFT BLANK Feb 25 2005 7 13 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 7 13 GROUND CONTROL The directional control of the aircraft on the ground is accomplished by differential breaking of the main gear wheels The brakes are actuated by pushing the upper part of the appropriate rudder pedal Use of the right brake pedal has a breaking effect on the right main gear wheel and will steer the nose to the right Use of the left brake pedal has a braking effect of the left main gear wheel and will steer the nose to the left The braking force depends upon the intensity of the pressure applied to the brake pedals 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 decelerate the aircraft in a straight line a uniform pressure should be applied simultaneously to both brake pedals CAUTION _ GJ Before every takeoff and landing ens
61. 5 1066 2641 1099 4000 2428 984 2493 1017 2575 1066 2641 1099 2707 1132 5000 2493 1017 2559 1050 2641 1083 2707 1132 2789 1165 6000 2543 1050 2625 1083 2707 1132 2772 1165 2854 1198 7000 2608 1083 2690 1115 2772 1165 2854 1198 2936 1247 8000 2674 1115 2756 1148 2838 1198 2936 1247 3018 1280 NOTES 1 THE LANDING PROCEDURE FOR SHORT FIELDS IS DESCRIBED IN SECTION 4 2 DECREASE DISTANCES BY 10 FOR EVERY 10 KNOTS OF HEADWIND FOR OPERATION WITH TAILWINDS UP TO 10 KNOTS INCREASE DISTANCES BY 10 FOR EVERY 2 KNOTS 3 INCREASE GROUND ROLL ON DRY GRASS SURFACE BY 35 4 FOREACH DEGREE OF RUNWAY SLOPE INCREASE GROUND ROLL BY 15 5 WITH FLAPS UP V 7 4 KIAS INCREASE LANDING DISTANCE BY 45 EXAMPLE M TOTAL OVER 50 FT OBSTACLE 2461 ft WEIGHT 2150 lbs GROUND ROLL 1001 ft AIR TEMPERATURE 33 C AIRFIELD PRESSURE ALTITUDE 1000 ft THE CORRECTION FOR HEADWIND HEADWIND COMPONENT 10 kts 10kts 10 kts x 10 10 DECREASE READ VALUE AT ISA 20 C BECAUSE THE STANDARD TOTAL OVER 50 FT OBSTACLE 2215 ft TEMPERATURE IN 1000 FT IS 13 C 13 20 33 C GROUND ROLL 901 ft NJ Figure 5 12 5 24 Feb 25 2005 Symphony SECTION 6 SA 160 WEIGHT AND BALANCE 6 1 6 3 6 5 6 7 6 9 SECTION 6 WEIGHT AND BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page CET l sa I EE E E A tiro 6 2 Aircratt Weighing Proce
62. 969 2444 2083 2575 2182 2690 2297 2822 8000 2001 2477 2116 2608 2231 2740 2329 2871 2444 3002 NOTES 1 THE TAKEOFF PROCEDURE FOR SHORT RUNWAYS IS DESCRIBED IN SECTION 4 2 DECREASE DISTANCES BY 10 FOR EVERY 9 KNOTS OF HEADWIND FOR OPERATION WITH TAILWINDS UP TO 10 KNOTS INCREASE DISTANCES BY 10 FOR EVERY 2 KNOTS OF 3 FOR OPERATION ON DRY GRASS RUNWAY INCREASE DISTANCES BY 10 OF THE GROUND TAILWIND ROLL FIGURE EXAMPLE WEIGHT 2150 Ibs AIR TEMPERATURE 21 C AIRFIELD PRESSURE ALTITUDE 2000 ft HEADWIND COMPONENT 13 5 kts READ VALUE AT ISA 10 C BECAUSE THE STANDARD TEMPERATURE IN 2000 FT IS 11 C Ir d GROUND ROLL 1394 ft OVER A 50 FT OBSTACLE 1755 ft THE CORRECTION FOR HEADWIND 13 5 kts 9 kts X 10 15 DECREASE 11 107 21 C GROUND ROLL 1185 ft OVERA50 FT OBSTACLE 1492 ft Figure 5 6 Feb 25 2005 5 17 Symphony SECTION 5 anony PERFORMANCE SA 160 RATE OF CLIMB CONDITIONS FLAPS 0 FULL THROTTLE RATE OF CLIMB FT MIN wei MS cu Ibs f KIAS ISA ISA ISA ISA ISA t 10 C 10 C 20 C 30 C MSL 80 740 710 680 655 630 2000 78 645 615 590 560 535 4000 76 550 520 495 470 445 2150 6000 74 455 425 400 375 350 8000 73 365 340 315 290 270 10000 73 270 245 220 195 175 12000 73 175 150 130 105 MSL 80 995 965 930 900 870 2000 78 890 860 830 800 770 4000 76 790 755 725 700 670 183
63. 97 psi 0 5 psi 8 psi AVGAS 100LL aviation oils see section 8 para 8 11 1 MT Propeller MT 186 R 140 3D 1 854 m 73 in 2700 RPM Feb 25 2005 SECTION 2 LIMITATIONS Symphony SA 160 2 9 ENGINE PARAMETER COLOR MARKINGS OS L 2 5 V SdNV 6 LE 8 82 182 0 vc SOA DL 00 L do 193 00S 9 p Sev OSL do LHO 08 90 ISd Saud 131 9 2 Hd9 MO TH Dr Sve S do dW31 llo 26 96 G6 GG ISd Saud 110 OLE 162 0 62 O EL 9H Saud NVA 0022 0090 NIA 1 Wd Q3LI8IHOHd OHV day Hdddn HO LVOIGNI OOOL WA AHL NO SONDIHVIN HOTOD YILIINVEAVA 3NION3 NOLLNVO DY MOTA Hdddn 39NvH SNI1VH3dO TVINHON OYV N3349 INOLLNVD DH V MOTI3A MoT aaLIgIHO Hd O4V day MO1 Jo oUEJEd Feb 25 2005 SECTION 2 gt ymphony LIMITATIONS SA 160 2 11 WEIGHT LIMITS a Maximum Ramp Weight 975 kg 2150 Ibs b Maximum Takeoff Weight 975 kg 2150 Ibs c Maximum Landing Weight 926 kg 2042 Ibs d Maximum Weight in Baggage Compartment 75 kg 165 Ibs but in the front or rear area maximum 45 kg 99 Ibs NOTE For dependence maximum weights on performance see Weight kg Ibs 648 1428 975 2150 NOTE section 5 Performance 2 13 CENTER OF GRAVITY LIMITS Forward Aft m in aft of m in aft of Datum Datum 2 45 96 46 2 60 102 36
64. A 160 7 39 STATIC AND PITOT PRESSURE SYSTEM The static and pitot pressure system supplies pitot and static pressure for the airspeed indicator the altimeter and the vertical speed indicator See fig 7 16 The aircraft dynamic pressure is picked up by the pitot tube installed on the underside of the left wing and carried through a line inside the wing strut and fuselage to the relevant instruments on the panel The static pressure source is performed by two static ports on the left and right side of the fuselage before the empennage The static pressure reaches the instrument panel via a static pressure line in the fuselage The pitot tube head is equipped with a heating element to prevent icing during the flightin potential icing conditions Pitot tube heating is activated switching the PITOT HT switch on the ON position Illumination of an amber PITOT HT OFF caution light IFR located on the upper instrument panel left to the EC 100 indicates that the pitot heater is not operational Both the pitot and the static pressure lines can be drained through separate drain valves located on the bottom of the fuselage A cover should be placed over the pitot tube while the aircraft is parked outside to prevent insects and water from entering the pitot orifice A partially or completely blocked pitot vent will result erroneous erratic or zero readings on the associated instruments CAUTION Make sure that the pitot cover is
65. CT TO DESTINATION a Press the key A select direct to waypoint page will appear with the waypoint identifier field highlighted b Use the small and large E right knobs to enter the identifier of the desired destination waypoint c Press to confirm the selected waypoint and KE toactivate the direct to function 4 6 TO SELECT A NEARBY AIRPORT AS A DIRECT TO DESTINATION a Press to display the select direct to waypoint page b Rotate the large right knob 6 to place the flashing cursor on the nearest airport NRST field c Rotate the small right knob 6 to display a window listing up to nine nearest airports Feb 25 2005 9 of 15 SECTION 9 gt ymphony IRCRAFT SUPPLEMENT 2 SA160 d Continue rotating the small right knob desired airport to highlight the e Press EN to accept the selected waypoint s identifier and press a second time with Activate highlighted to begin navigating to the selected waypoint 4 7 GNC 420 Integration The GNC 420 system is integrated into the aircraft avionics installation in two configurations a Single GNS 430 GPS 1 interfaced with the CDI VOR LOC ILS GS Indicator and a 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 LOC Indicator In this configuration GNC 420 GPS course information is displa
66. DDER CONTROL SYSTEM Figure 7 3 Rudder Control System 7 10 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 7 9 INSTRUMENT PANEL The instrument panel of the SA 160is shownin Fig 7 4 For an easy and quick reference the instruments and controls are clearly divided in three sections left centre and right sections The left section is comprised of a group of six flight instruments located in front of the pilot for further details se Fig 7 4 Below the flight instrument is a row of switches for system command The middle section of the panel contains the avionics equipment The avionics equipment type is depended upon the configuration of the aircraft i e VFR or IFR version Below the avionics equipment is the throttle mixture and carburetor heat On the center console pedestal is located the flap switch and next to it the light dimmer switches On the lower part of the pedestal are the heat controls the fuel shut off valve the primer and the parking brake control buttons The VM 1000 Engine Management System indicator is on the right side of the avionics column It shows the manifold pressure the engine speed oil temperature oil pressure cylinder head temperature exhaust gas temperature fuel pressure as well as alternator output amperage and voltage of the electrical system The circuit breaker panel is located on the extreme right side of the panel 7 11 FLIGHT INSTRUMENTS Flight instrume
67. Distance to Clear 50 ft Obstacle 5 8 Feb 25 2005 Symphon Y SECTION 5 SA 160 PERFORMANCE a Approximation Method Read values at 2150 lbs ISA 30 C and 2000 ft Lift Off Speed 58 KIAS Speed at 50 ft 62 KIAS Ground Roll 1575 ft Total to Clear a50 ft Obstacle 1985 ft b Interpolation Method The example airfield pressure altitude is 20 of 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 Off Speed 58 KIAS Speed at 50 ft 62 KIAS Ground Roll 1562 ft Total to Clear a50 ft Obstacle 1960 ft The correction for headwind For a 10 kts headwind decrease distances by 10 Ground Roll 1562 ft 10 x 1562 ft 1406 ft Total to Clear a50 ft Obstacle 1960 ft 10 x 1960 ft 1764 ft Feb 25 2005 5 9 SECTION 5 gt ymphony PERFORMANCE SA 160 5 9 PERFORMANCE CHARTS AIRSPEED CALIBRATION CONDITIONS KIAS ASSUMES ZERO INSTRUMENT ERROR FLAPS KIAS 65 75 85 95 105 115 125 gt 135 00 KCAS 64 74 84 94 107 115 126 gt 135 FLAPS KIAS 55 60 65 70 80 90 20 KCAS 54 59 64 70 80 90 FLAPS KIAS 55 60 65 70 80 90 40 KCAS 54 59 64 70 80 90 3 Kias Knots Indicated Air Speed Kias Knots Calibrated Air Speed EXAMPLE FLAPS 20 INDICATED AIRSPEED 60 KIAS CALIBRATED AIRSPEED 59 KCAS Figure 5 1 1
68. E PARAMETERS AND FLIGHT PLANNING INTRODUCTION The performance information on the following pages shows what is to be expected of the aircraft under various conditions They are also a means for sufficient and correct flight planning The data has been computed from extensive flight tests with the aircraft and engine in good condition and is approximated to average piloting techniques Effects of ambient conditions such as a soft or grass runway surfaces fortakeoff and 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 profile charts allow for 45 minutes of reserve fuel at the specified power settings Fuel consumption is based on flight with appropriate leaning techinque for the mixture at different altitudes The recommended procedures for leaning mixture are explained in Section 4 4 7 AMPLIFIED NORMAL PROCEDURES of this handbook Due to the various influences on fuel consumption during flight use all available information check fuel flow and quantity frequently while in flight To obtain the performance indicated in the charts follow the chart procedures This section contains a flight planning example This example shows the order as well as the manner in which to perform flight planning with reasonable accuracy by using the performance charts and tables In addition each chart i
69. ED COLUMN 5 ft 2 INFLUENCE OF THE CABIN HEAT IS FOUND TO BE NEGLIGEABLE EXAMPLE FLAPS 0 INDICATED AIRSPEED 90 KIAS ALTIMETER CORRECTION 50 ft Figure 5 2 2 Feb 25 2005 5 13 SECTION 5 PERFORMANCE Symphony IRCRAFT SA 160 TEMPERATURE CONVERSION 120 100 80 60 40 DEGREES FAHRENHEIT 20 40 20 0 20 DEGREES CELSIUS Figure 5 3 5 14 40 60 Feb 25 2005 Symphony AIRCRAFT SA 160 SECTION 5 PERFORMANCE LITERS GALLONS CONVERSION 60 50 40 Liters 30 Feb 25 2005 A m m m m ua O N AR A NO A OG O 0 Gallons Figure 5 4 Liters 120 90 80 70 60 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 Gallons Symphony SECTION 5 IRCRAFT PERFORMANCE SA 160 STALL SPEED CONDITIONS POWERIDLE WEIGHT 975 kg 2150 Ibs Most forward C G Position STALL SPEEDS KNOTS CONDITIONS ANGLE OF BANK o 307 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS FLAPS 60 59
70. ED 9 Cabin EIeat c onere eno eie ome ri Don Tea eee OFF 4 Fire Extinguisher as required sss ACTIVATE 5 Allother Switches except ignition switch tette OFF WARNING GJ After fire is completely extinguished ventilate cabin If it cannot be visually determined that the fire is completely extinguished land as soon as possible After ascertaining that fire has been extinguished completely 6 Cabin ventilada FULL OPEN 7 Switch ALT 7 BAD aa wani rs re ded ON 8 Circuit Breakers acier dba kok eee etre A CHECK If the short circuit is localized 9 Required electrics o nette eene etui ON 10 Land as soon as practical to inspect damages k Loss Of Oil Pressure Land as soon as possible Oil Temperature uwaa zwano teet epe rep qme edes CHECK Prepare for Landing Without Engine Power d 3 8 Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES I Power Supply System Malfunction Ammeter and voltmeter shows a power supply system malfunction AFL SW E iza E Jod CHECK ON 2 ALT BED circuit breaker ovinos CHECK and reset as required 39 ALD WIEC EE OFF then ON If power of alternator is not restored Ke D WE El EE OFF 5 Non essential electrical equipment sss OFF 6 Land as soon as practical m Excessive Rate Of Charge Ammeter and voltmeter shows a excessive rate of charge Ty ALF Within M OFF 2 N
71. ENDIX KING FUNCTION SELECTOR CONTROL KNOBS IDENT PUSHBUTTON Figure 7 19 Transponder Front View Feb 25 2005 7 55 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 7 47 EMERGENCY LOCATOR TRANSMITTER ELT The SA 160 comes equipped with an Artex ELT 200 emergency locator transmitter The ELT activates automatically during a crash or manually by a remote switch The ELT transmits the standard swept tone on international distress frequencies of 121 5 MHz and 243 0 MHz 00000 000000 00000 000000 00000 00000 o 00000000 O Red LED TEST RESET PRESS ON WAIT 1 SECOND PRESS ARM Figure 7 20 ELT Remote Switch Annunciator 7 56 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION The ELT unit itself is located in the fuselage behind the cabin just over the battery Itisaccessible through the baggage door The ELT can be manually operated by the flight crew using the 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 is transmitting The emergency transmitter works independently from the power supply of the aircraft since it has its own battery For complete operating instructions refer the Artex ELT 200 Installation and Operation Manual publishe
72. Feb 25 2005 5 of 11 SECTION 9 gt ymphony SUPPLEMENT 3 SA160 b LEFT LARGE KNOB O Pilot ICS mic VOX squelch level Clockwise rotation increases the amount of mic audio VOX level required to break squelch Full counterclockwise is the HOT MIC position c RIGHT SMALL KNOB O Copilot ICS volume d RIGHT LARGE KNOB O Copilot mic VOX squelch level Clockwise rotation increases the amount of mic audio VOX level required to break squelch Fully counterclockwise is the HOT MIC position NOTE Audio level is always controlled be the selected COM or NAV radio volume 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 pilot for MIC audio while COM 2 is dedicated to the copilot for MIC audio The pilot and copilot can simultaneously transmit in this mode over separate radios Both pilots can still listen to COM 3 NAV 1 NAV 2 DME ADE and MKR as selected The Split COM mode is canceled by pressing the COM 1 2 button asecond time 4 6 SELECT A NAV AUDIO SOURCE Press NAV 1 NAV 2 DME ADF or MKR to select each audio source A second button press deselects the audio 6 of 11 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 3 SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in the paperwork delive
73. G GJ Do notoperate the engine until excess solvent has evaporated or otherwise been removed WARNING GJ Before rotating the propeller by hand ensure ignition switch is OFF mixture control is in the IDLE CUT OFF position and the throttle is closed 11 Before starting engine rotate the propeller by hand in the direction of normal rotation no less than five complete revolutions e Interior To remove dust and loose dirt from seats and carpet clean the interior regularly with a vacuum cleaner Interior panels such as sidewalls door panels etc may be cleaned using a mild detergent solution Stubborn deposits may be removed using a suitable material cleaner in accordance with manufacturer s instructions If in doubt apply a small amount of cleaner to a small unobtrusive part and test it for reaction The instrument panel and center pedestal can be wiped with a slightly moistened cloth CAUTION Ensure the ALT BAT switch is in the OFF position Feb 25 2005 8 16 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 For cleaning and care of the seat upholstery use foam type detergent such as is commercially available for car seats Follow the manufacturer s instructions Oil spots may be removed with household spot removers Read the manufacturer s instructions on the container test it to an inconspicuous place and use it
74. HT ENEE 40 Cabin Doors UNLATCH PRIOR TO TOUCHDOWN Touchdown on water surface should be made at lowest possible airspeed with maximum angle off attack e szerzy EPEE AEO EVACUATE 8 Inflate Life Vests and Raftwhen clearofaircraft emt WN N Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES h Engine Fire During Engine Start i 1 8 9 10 Ignition SWIECA CRANK ENGINE If engine starts Keep throttle for a few minutes at 1800 RPM A A iip n niai endi ces SHUTDOWN and inspect for damage If engine fails to start Ignition Switch CONTINUE CRANKING ENGINE A ee FULL OPEN EK ENEE IDLE CUT OFF puel Valve zaa dna net metre ia eire te OT EE OFF If fire continues SAULT BAI iacente eniti ise tret teri Her a io Hee OFF Fire Extinguishet iet ai USE Aircraft M EVACUATE Engine Fire In Flight 9o un PWN Pr N Fuel Valve ucraniana OFF A e Preterea eene re en CLOSED MIRTE cire ete rre inis IDLE CUT OFF Aux Fuel PUN Praia OFF Cabin E E OFF Cabin Ventilation for Lowest SMOKE in Cabin nitritos SET Inform the corresponding ground station SHEET OFF Fire Extinguisher as reoguired esses ACTIVATE Proceed with Y Landing Without Engine Power d Feb 25 2005 3 7 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 j Electrical Fire In Flight T OWC NS A eeben OFF 2 Cabin Ventilationza idee ditt entretenir o CLOS
75. It is also used to confirm information such as during power on The large right knob is used to select between the various Page groups NAV WPT AUX or NRST With the on screen cursor enabled the large right knob allows moving the cursor about the page The small right knob E is used to select between the various pages within one of the groups listed above Press this knob momentarily to display the on screen cursor The cursor allows entering data and or making a selection from a list of options 14 of 16 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 1 3 Bottom Row Keys The CDIkey is used to toggle which navigation source GPS or VLOC provides output to an external HSI or CDI The OBS key UB is used to select manual or automatic sequencing of waypoints Pressing the OBS key selects OBS mode which will retain the current active to waypoint as the navigation reference even after passing the waypoint i e prevents sequencing to the next waypoint Pressing the OBS key again will return to normal operation with automatic sequencing of waypoints Whenever OBS mode is selected the user may set the desired course to from a waypoint using the OBS Page or an external OBS selector on the HSI or CDI The message key Hj is used to view system messages and to alert the pilot to important warnings and requirements The flight plan key allows creating editing activating and inverting flight plans as well as ac
76. KING DME KN 62A This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and LBA Approved Airplane Flight Manual when the Bendix King DME KN62A hasbeeninstalled The Information contained herein supplements or supersedes the basic Pilot s Operating Handbook and LBA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Date 4 rect Approved Transport Canada lp aa Issued Feb 25 2005 Symphon Y SECTION 9 SA 160 SUPPLEMENT 5 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective 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 6 Feb 25 05 2 of 6 Feb 25 05 3 of 6 Feb 25 05 4 of 6 Feb 25 05 5 of 6 Feb 25 05 6 of 6 Feb 25 05 Feb 25 2005 i SECTION 9 gt ymphon Y SUPPLEMENT 5 SA 160 LIST OF REVISIONS Rev Date Page Na No Description ii Feb 25 2005 Symphon Y SECTION 9 SA 160 SUPPLEMENT 5 SUPPLEMENT 5 TABLE OF CONTENTS SECTION PAGE GENERAL 220505 6s paw ee SE ar ea Aa 2 of 6 LIMITATIONS 5 44 e ex BASS Se ee YA 3 of 6 EMERGENCY PROCEDURES 3 of 6 NORMAL PROCEDURES 3
77. Lycoming Service Instruction No 1014 MIL L 6082 Aviation Grade Straight Mineral Oil and MIL L 22851 Aviation Grade Ashless Dispersant Oil should be used Oil Viscosity Recommended viscosity of oils for air temperature range Mean Environment MIL L 6082 MIL L 22851 Temperature Mineral Ashless Dispersant Above 16 C SAE50 SAE 40 or SAE 50 1 C 30 F to 32 C SAE 40 SAE 40 18 C 0 F to 21 C SAE 30 SAE 30 or SAE 40 Below 12 C SAE 20 SAE 30 Capacity The engine has a oil capacity of 7 6 Litres 8 quarts but it must not be operated on less than 5 Litres 5 2 quarts Oil and Oil Filter Change 1 The SA 160 is delivered with straight mineral engine oil MIL L 6082 If the oil level is topped up within the first 25 hours of 8 9 Feb 25 2005 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE operation engine oil of the same specification and of the same recommended viscosity must be used MIL L 6082 After 25 hours of operation an oil and oil filter change is required Refill the sump again with straight mineral oil and use until a total of 50 hours has accumulated or oil consumption has stabilized After this an oil and filter change is to be carried out and ashless dispersant oil MIL L 22851 should be now be used 2 For oil and oil filter change time intervals refer to Lycoming Operator s Manual and appropriate Lycoming Service Instruction Lubricating Oil Recommendations latest issu
78. ME Le SZER A 44 2 in B B 113 3 in POSITION SYMBOL SCALE READING SCALE ERROR NET WEIGHT lbs NOSE WHEEL N RIGHT MAIN WHEEL R LEFT MAIN WHEEL L AIRCRAFT TOTAL AS WEIGHED Empry Weight We Center of Gravity C of Gw Empty Weight Me We N L R Cof Gw N A R L B Me We x C of Gw We BASIC EMPTY WEIGHT AND C G ITEM WEIGHT lbs C G ARM in MOMENT in lbs BASIC EMPTY WEIGHT The standard empty weight includes the required oil level 8quarts and 2 4 US Gal unusal Figure 6 1 Feb 25 2005 ble fuel 6 5 SECTION 6 gt ymphony WEIGHT AND BALANCE SA 160 Marked Hole Static Port Hole Figure 6 2 Markings for Aircraft Longitudinal Leveling 6 6 Feb 25 2005 Symphony SECTION 6 SA 160 WEIGHT AND BALANCE d Basic Empty Weight Center of Gravity 1 The basic empty weight We as weighed including equipment noted in the equipment list required oil level and unusable fuel is given by We N L R where N Nose wheel net weight lbs R Right main wheel net weight lbs L Left main wheel et weight Ibs 2 The center of gravity C of Gw corresponding to the basic aircraft empty weight is given by C of Gw N A R L B We where A Distance from nose wheel from reference datum 44 2 In B Distance from right and left main wheel from reference datum 113 2 In 3 The empty weight m
79. N 7 Symphon Y DESCR amp OPERATION SA 160 7 27 PROPELLER The aircraft is equipped with a fixed pitch composite two blade MT Propeller The propeller composite construction consists of multiples laminated and plastic covered ash wood strips with bonded stainless steel metal tips The Propeller has a diameter of 1 854 m 73 in and a pitch of 9 mm 0 35 in at0 75 blade radius 7 30 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 7 29 FUEL SYSTEM The fuel system of the SA 160 See Fig 7 9 consists of two main fuel tanks which are installed in the wings a feeder tank behind the seats a fuel shut off valve on the center pedestal an auxiliary fuel pump a gascolator an engine driven fuel pump and a single barrel float type carburetor in the engine compartment Fuel lines are made of flexible hoses and aluminum depending upon location The fuel system quantities are as follow Fuel Quantity Data Total Fuel 123 1 32 5 U S Gallons Usable Fuel 114 1 30 2 U S Gallons Unusable Fuel 91 2 3 U 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 support fuel supply in case of the failure of the engine driven pump Fuel flows from the two wing tanks through flexible hoses and aluminum fuel lines to air bleeder tubes and to the feeder tank The feeder tank guarantees a continuous f
80. NED CHECK E c FULL RICH Aux Fuel PUMP ert rte nente tee ri ON Carburetor Heat siii anida ON Landing Ligier terrere ee arte e tede geri ON dri E M M M As required SET l EE SET Parking Brake Control Knob optional CHECK PUSHED IN Final Approach Speed Flaps 40 za aaa yanki moba pia eius 65 KIAS NOTE It is recommended that all necessary landing checks and actions in the cabin are completed before turning 4 14 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES on to the final approach In this way the pilot s attention can be directed completely to controlling the aircraft o Landing Normal Conditions dE PAPA uu A o A PO 40 APs POO ea dE O o AA iei eor cun 65 KIAS Flare the aircraft so that it flares out at approx 0 5 m over and parallel to the runway surface Increase pitch with decreasing speed so that the aircraft slowly approaches the ground and make contact with the lowest possible speed main wheels first After touchdown Nose Wheel ii O LOWER GENTLY Braking sa aoi re ee eie timere AS REQUIRED Balked Landing Blei FULL OPEN Carburetor He atinada iaa dd OFF Airspeed iii mete eter ted Stabilize 65 KIAS MUTA ves Seeds SET After reaching the safety height of 50 ft leegen RETRACT p After Landing Bleech RETRACT Carburetor Feat iae dnm ertet edet ed O W Ani OFF
81. NIC 1 switches in ON position IFR The transponder will turn on in the standby mode After power on a start up page will be displayed while the unit performs a self test Feb 25 2005 3 of 8 SECTION 9 gt ymphony SUPPLEMENT 4 SA160 4 2 SELECT A TRANSPONDER MODE a To select the standby mode press STBY key Powers on the transponder in standby mode At power on the last active identification code will be selected When in standby mode the transponder will not reply to any interrogations b To select the Mode A press the ON key Powers on the transponder in Mode A At power on the last active identification code will be selected In this mode the transponder replies to interrogations as indicated by the Reply Symbol Replies do notinclude altitude information c To select the Mode C press the ALT key Powers 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 indicated by the Reply Symbol Replies to altitude interrogations include the standard pressure altitude received from an external altitude source which is not adjusted for barometric pressure The ALT mode may be used in aircraft not equipped with the optional altitude encoder however the reply signal will not include altitude information 4 3 CODE SELECTION GGGGO aaa Code selection is done with eight keys 0 7
82. OFF Trote edente tne Rn Re 1000 1200 RPM bur ll CHECK ED PEeSSHIGS acz tad n re mee PUR Eege CHECK Oil Temperature eene teet retener perite CHECK Fuel Pressure c ee orae eso i e e OR ALA CHECK Feb 25 2005 4 11 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 i Before Takeoff luci M APPLY A enne pure etri eredi ido ien 1000 1200 RPM Iri E E ENGAGED Seat Belts and Harnesses sess FASTENED CHECK Empty Seat siitoin Seat Belts SNUGLY FASTENED Cabin DOorts ses aeneis CLOSED AND LATCHED Instrument Map Light at Niebt sss ADJUST PEW RE nie nii tige e peso eei ie oi ais LOCKED Fuel Valve aa ii oen ie E d t EE IHRER ROUES CHECK ON Pitot Heat nit etie res ie e PORE HT Eos SU ON Aux Fuel Pup nta rca ON Fuel Quantity ies iier AAA CHECK IMIXEUTE Sore Suet e diede etiem n tera de NA RR FULL RICH Carburetor Feat ette ea etes OFF Ignition AAA o BOTH Engine Parameters E CHECK Flight Instruments sees adjust and CHECK Navigation Equipment ssessessssrseresseseese OPERATIONAL as required TEL E aid O ON SET j Takeoff Normal Conditions PIAS PORE 20 lici RELEASE THROES C A E A eech FULL OPEN Ataspeed of 53 KIAS ntc aia ROTATE to lift off After lift off accelerate to Airspeed insisto 65 75 KIAS After an altitude of 50 ft is achieved 4 12 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES Win
83. ORMAL PROCEDURES SA 160 Static Discharger 11111 CHECK for security of attachment and general conditions Flap and Aileron iet ttes CHECK for freedom of movement and security Bonding Straps CHECK for security of attachment and general conditions 20 Flap Position Color Marking on Flap Track CHECK for condition Right Side Top Deck Hatch CHECK for security Fuel Tank Gang hte DRAIN fuel into clear cup puel sene RIGHE EIS CHECK for water sediment and proper fuel Right Main Gear Strut and Wheel Fairing ss sss1sse1ss11se0s000e CHECK Main Wheel Tire nius a ance a AA W CHECK 5 Fuselage Fuselage Skins CHECK for stress cracks and fractures E EE CHECK peter ee eege CLEAR of ICE FROST SNOW Elevator CHECK for freedom of movement and security AIM JAD se etre O teda CHECK for integrity Rudder CHECK for freedom of movement and security Static Dischargers 11111 CHECK for security of attachment and general conditions Baggage Compartment CHECK baggage anchored down Baggage DOO accociociconscrciriici narices CLOSED AND LOCKED At fuselage bottom Fuel System Low Point Drain DRAIN fuel into clear cup Pelican sii CHECK for water sediment and proper fuel Static Dynamic System Drain Valve
84. PERATURE 11 C FUEL 1 95 0 58 137 U S Gal CRUISE PRESSURE ALTITUDE 6000 ft DIST 145 NM 4NM 10 5 NM Figure 5 8 Feb 25 2005 5 19 SECTION 5 gt ymphony PERFORMANCE SA 160 CRUISE PERFORMANCE CONDITIONS WEIGHT 975 kg 2150 Ibs LEAN MIXTURE UP TO 75 POWER FOR BEST ZERO WIND ISA ECONOMY AND ADJUST FULL RICH ABOVE 75 Pressure Standard Temperature Altitude ft RPM BHP KTAS Vn U S GAL h Minimum 2000 2700 92 5 128 48 12 7 2600 83 8 123 43 11 4 2500 75 6 118 33 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 2100 50 6 101 22 5 8 2000 40 0 88 18 4 8 6000 2700 81 3 128 42 11 1 2600 72 5 123 32 8 5 2500 66 3 118 29 7 2400 60 0 114 26 6 9 2300 53 8 107 24 6 3 2100 47 5 101 21 5 5 2000 38 1 88 17 4 5 8000 2700 73 8 128 32 8 5 2600 67 5 123 30 7 9 2500 61 9 118 27 i 2400 56 9 114 25 6 6 2300 50 0 107 22 5 8 2100 45 6 101 20 5 3 2000 36 9 88 16 4 2 Figure 5 9 1 5 20 Feb 25 2005 Symphony AIRCRAFT SECTION 5 SA 160 PERFORMANCE CRUISE PERFORMANCE Continued Pressure Standard Temperature Altitude ft RPM BHP KTAS l h U S GAL h Minimum 10000 2700 S s 2600 63 1 123 28 7 4 2500 56 9 118 25 6 6 2400 53 8 114 24 6 3 2300 46 9 107 21 5 5 2100 43 1 101 19 5 0 2000 35 0 88 15 4 0
85. PERFORMANCE 5 1 5 3 5 5 5 7 5 9 SECTION 5 PERFORMANCE TABLE OF CONTENTS Page E E oi A 5 2 Introduction to the Performance Parameters and Plight Planning ws di ia 5 2 Flight Planning Example trt 5 3 a Iak60ff ote ete ii 5 4 D C EUISC itae EEE A DUE Ri tret iare e dest 5 4 c Fuel Required vocacionales 55 AA A Td 5 6 Use of Performance Charts saa doda preteen 5 8 a Approximation Method 5 9 b Interpolation Method honte en emetne 5 9 Performance C hats etit teneret tere eei eene 5 10 Fig 5 1 Air Speed Calibration emen 5 10 p2 Altimeter Correction 5 12 5 3 Temperature Conversion meserii 5 14 5 4 Liters Gallons Conversion eee 5 15 bib Stall Spec Sarria w hee et AE 5 16 5 6 Takeoff Distance for short Helde 5 17 b 7 Rate OF CHAD EE 5 18 5 8 Time Fuel and Distance to Climb sss 5 19 5 9 Cruise P rformarece inei ime rentrer eiii Rein 5 20 5 10 Best Range Profile eie iia 5 22 5 11 Endurance Profile untar tenet 5 23 5 12 Landing Distance for short fields 5 24 Feb 25 2005 5 1 SECTION 5 gt ymphony PERFORMANCE SA 160 5 1 GENERAL This SECTION contains all the prescribed performance data as well as supplementary information for this aircraft Performance data for optional equipment that requires handbook supplements is provided in Section 9 SUPPLEMENTS 5 3 PERFORMANC
86. RES 3 of 8 PERFORMANCE 3 5 5 25 6604 24 20d miner ge S s 5 of 8 WEIGHTANDBALANCE 5 of 8 DESCRIPTION AND OPERATION 5 of 8 Feb 25 2005 1of8 SECTION 9 gt ymphony SUPPLEMENT 4 SA160 SECTION 1 GENERAL 1 1 INTRODUCTION The Garmin GTX 327 Transponder located mid avionics panel receives interrogations from a ground based secondary radar transmitter and transmits the aircraft s identification to the Air Traffic Control Center via Mode A transmissions and altitude information via Mode C 1 2 SPECIFICATIONS Power Requirements 11 0 to 33 0 Vdc Power Input 15 W typical Transmitter Frequency 1090 MHz Transmitter Power 150 W Nominal Receiver Frequency 1030 MHz Receiver Sensitivity 72 dBm Nominal Mode A Capability 4096 Identifications Codes Mode B CapabilityE 100 Foot Increments from 1000 to 63 000 feet GTX Unit Weight 2 39 Ibs Altitude 50 000 feet 2 of 8 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 4 SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES No change SECTION 4 NORMAL PROCEDURES Normal operating procedures are completely described in the GARMIN GTX 327 Mode A C Transponder Pilot s Guide P N 190 00187 00 Rev A or later appropriate revision NOTE The GTX 327 Mode A C Transponder is shown in figure 7 1 4 1 POWERING ON THE GTX 327 Place BAT and AVIONIC switches in ON position VFR Place BAT and AVIO
87. S Land straight ahead make only shallow turn to avoid obstructions if possible MUXTUTE D M IDLE CUT OFF Fuel Valve niai ROG tia OFF Ignitioti OWIEC EE OFF Switch ALT BAT s tano ciao OFF c Engine Failure During Flight Restart Procedures 3 4 1 UB PD Establish glide secure airspeed of 74 KIAS Locate suitable field At sufficient flight altitude E wes CHECK FULL RICH AUX Fuel PUMP iii ON Carburetor Heat az ada w w m i adi ON Ignition Witch ninia ya ren BOTH Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES 6 Fuel Valve coin CHECK ON 7 Fuel Quantity odci w NA EA PO CHECK 8 Engine Parameters mccc asaan CHECK 9 If propeller is stopped V 70 KIAS Ignition switch shortly ee START to initiate autorotation If power is not restored prepare for Landing Without Engine Power d d Landing Without Engine Power Te Airspeed ironia ati 74 KIAS 2 Seat Belts and Harnesses AWA A TIGHT 9 ADS ses awa its as required SET Before landing d MAXHUTE we c O EE O EE IDLE CUT OFF 5 TE OFF 6 Ignition SW sese eee O A i OFF Le WIR DR KEE OFF Touchdown with lowest possible airspeed 8 DOTS tAcwdaiithdenws UNLATCH PRIOR TO TOUCHDOWN 9 Brakes as required iii ici APPLY e Rough Engine Operation PWN Pe 8 Carburetor Heat inician atra ON Aux Fuel PUMP aaa ti teens ON MIXTUNE sss ADJUST for MAXIMUM SMOOTHNESS leur
88. Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time Feb 25 2005 1 9 SECTION 1 gt ymphony GENERAL SA 160 b Meteorological Terminology ISA International Standard Atmosphere in which 1 The airis a dry perfect gas 2 The temperature at sea levelis 15 Celsius 59 Fahrenheit 3 The pressure at sea level is 29 92 inches h g 1013 2 mb 4 The temperature gradient from sea level to the altitude at which the temperature is 56 5 C 69 7 F is 0 00198 C 0 003564 F per foot and zero above that altitude OAT Outside Air Temperature is the free air static temperature obtained either from inflight temperature indications or ground meteorological sources adjusted for instrument error and compressibility effects MSN Mean Sea Level Indicated Pressure Altitude The number actually read from an altimeter when the barometric subscale has been set to 29 92 inches of mercury 1013 2 mb Pressure Altitude Altitude measured from standard sea level pressure 29 92 in hg by a pressure or barometric altimeter It is the indicated pressure altitude corrected for position and instrument error In this Handbook altimeter instrument errors are assumed to be zero Station Pressure Actual air pressure at field elevation 1 10 Feb 25 2005 Symphony SECTION 1 SA 160 GENERAL c Power Terminology Takeoff Power The maximum power permissible for takeoff may be t
89. Symphony AIRCRAF Ai Trois Rivi res Canada SYMPHONY AIRCRAFT INDUSTRIES Flight Manual SYMPHONY SA 160 REGISTRATION Category of Airworthiness Normal Applicable Airworthiness Requirements AWM Chapter 523 Serial No 023 042 amp S 0001 up Date of Issue Feb 25 2005 Document AFM SAI SA 160 101001 E This manual must be carried in the aircraft at all time Scope and revision status can be found in the list of Effective Pages and in the Record of Revisions The pages identified as DOT appr in the List of Effective Page are approved by Signatur ector Aircraft Certification Authority Transport Canada Date of approval Fe 25 Zoos This Flight manual contains the Transport Canada AW regulatory information required by CAR 523 and FAR 23 Compliance with Section 2 Limitations is mandatory Approved Transport Canada Issued Feb 25 2005 Symphony Aircraft Industries Symphony AIRCRAFT SA 160 APPLICABILITY REVISIONS APPLICABILITY This handbook contains information applicable to the model SA 160 aircraft designated by serial number and registration number shown on the title page All information is based on data available at the time of delivery of your aircraft by Symphony Aircraft Industries Inc NOTE A current handbook must be in the aircraft during flight It is the operator s responsibility to maintain the handbookin acurrent status Revisions The information in this handbook w
90. TS CONTENTS SECTION GENERAL 4096665 6 po hae Wz gk ow ok ad 1 LIMITATION yes he EP RA a ny xs 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE ota das Sway Hee 5 WEIGHT AND BALANCE EQUIPMENT DIST des fos way bog ee e oen s 6 DESCRIPTION AND OPERATION OF THE AIRCRAFT AND ITS SYSTEMS 7 HANDLING SERVICING AND MAINTENANCE o ee aaa e o y 8 SUPPLEMENT A uk daa 9 Feb 25 2005 xi Symphony AIRCRAFT SECTION 1 SA 160 GENERAL SECTION 1 GENERAL TABLE OF CONTENTS Page Durcratt VIEWS 9 robada 1 2 1 1 Introduction dd NEEN 1 4 1 3 Technical Data eere os 1 5 ENGINE ass A 1 5 Propeller coi 1 5 gek 1 5 Gp 1 6 Maximum Certificated Weight 1 6 Typical Aircraft Weights rhttees 1 6 Cabin and Entry DIMENSIONS sese 1 7 Daggape SDdC o eei RO ere e s is 1 7 Specific LoadiN civil linda 1 7 Other Dallas esi a a laica 1 7 1 5 Symbols Abbreviations and Terminology sss 1 8 a General Airspeed Terminology and Symbols 1 8 b Meteorological Terminology eee 1 10 c Power Terminology tete A CAE 1 11 d Engine Instruments either rediens 1 11 e Aircraft Performance and Flight Planning Terminology ems 1 11 f Weight and Balance eerte ttim 1 12 p Other Definitions entm i 1 14 Feb 25 2005 1 1 SECTION 1
91. The cursor allows entering data and or making a selection from a list of options Feb 25 2005 13 of 15 SECTION 9 gt ymphony SUPPLEMENTS SA160 2 Bottom Row Keys The NRST key displays the nearest airport page Then rotating the small right knob steps through the NRST Pages The OBS key gg is used to select manual or automatic sequencing of waypoints Pressing the OBS key selects OBS mode which will retain the current active to waypoint as the navigation reference even after passing the waypoint i e prevents sequencing to the next waypoint Pressing the OBS key again will return to normal operation with automatic sequencing of waypoints Whenever OBS mode is selected the user may set the desired course to from a waypoint using the OBS Page or an external OBS selector on your HSI or CDI The message key BB is used to view system messages and to alert the pilot to important warnings and requirements The flight plan key GB allows creating editing activating and inverting flight plans as well as access approaches departures and arrivals A closest point to flight plan feature is also available from the flight plan key The procedures key GQ allows selecting approaches departures and arrivals from the active flight plan When using a flight plan available procedures for departure and or arrival airport are offered automatically Otherwise the user may select the desired airport then the desired procedure
92. When anti freezing additive is used it must meet the specification MIL I 27686 It should be blended uniformly with fuel while refueling and should not exceed 0 15 by volume of refueled quantity and for effectiveness it should be blended at no less than 0 10 by volume For example 42 6 ccm 1 5 fl oz anti freezing additive per 38 Liters 10 U S Gallons fuel would fall in this range Use only blending equipment that is recommended by the manufacturer to obtain proper fuel mixing ratio In addition to the information in this section the manufacturer s blending instructions should be used 8 11 Feb 25 2005 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE CAUTION _ _ GJ Direct the anti freezing additive into the flowing fuel stream Start the additive feed after the start of refueling and stop before completion of refueling Assure that the concentrated additive never comes into contact with any aircraft painted surfaces Fuel additive cannot be used as a substitute for preflight draining of the fuel system drains see section 4 NORMAL PROCEDURES Preflight Check NOTE Some fuels have anti freezing additives included at the refinery so no further blending is required The supplier and or the specialists of the service station can offer information on the fuel composition 8 13 CLEANING AND CARE a Windshield and Windows For cleaning the windshield and the windows
93. When continuing to use GPS navigation position must be verified every 15 minutes using another IFR approved navigation system d RAIM IS NOT AVAILABLE on the Final Approach 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 the system will flag and no longer provide course guidance with approach sensitivity Missed 6 of 15 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 2 approach course guidance may still be available with 1 nautical mile CDI sensitivity by executing the missed approach e Emergency Frequency of 121 500 MHz In an in flight emergency depressing and holding the Comm transfer button for 2 seconds will select the emergency frequency of 121 500 MHz into the Active frequency window SECTION 4 NORMAL PROCEDURES Normal operating procedures are completely described in the GARMIN GNC 420 Pilot s Guide P N 190 00140 20 Rev A dated July 1999 or later appropriate revision NOTE The GNC 420is shown in figure 7 1 4 1 POWERING ON THE GNC 420 a Rotate the Com power volume knob clockwise to turn the unit on and set the desired radio volume c Awelcome page appears briefly and the unit will conduct a self test to ensure proper operation During the self test check for 1 CDl halfleft no flag 2 G S half no flag 3 TO From flag to 4 Bearing to 135
94. accessories has been designed for functionality and safety See Fig 7 14 The alternator output is connected to the main bus through a 50 amp circuit breaker The battery bus is connected to the battery or the external power source The main and battery bus are interconnected by a50 amp circuit breaker The avionic bus 1 is powered through the battery bus and the avionic bus 2 through the main bus a ALT BAT Switch The switch ALT BAT also named master switch is a split rocker type switch The master switch is located on the instrument panel on the extreme left of the row of switches The master switch is colored red Through the right half of the switch labeled BAT the battery and main bus bars are supplied with power All electrical devices connected to the main bus can then be activated If an external power source is connected to the aircraft the electrical power to the main bus is still done through the BAT switch The left section of the master switch the alternator ALT switch controls the alternator During start up the alternator is put into standby and when the engine is running the alternator powers all the electrical devices connected to the main and battery bus bars Normally both sides of the ALT BAT switch should be used Feb 25 2005 7 39 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 simultaneously However if a situation so demands it is possible to switch to either battery ON or alternator OFF only
95. ady flight speed at which the aircraft is controllable in the landing configuration WARNING GJ The maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced Linear interpolation may be used for intermediate gross weights Maneuvering speed should not be exceeded while operating in rough air 2 5 AIRSPEED INDICATOR MARKINGS Markings KIAS Remarks Red Line 162 Never exceed speed Maximum speed for all operations Yellow Arc 130 162 Operations must be conducted with caution and only in smooth air Feb 25 2005 2 3 Symphony SECTION 2 IRCRAFT LIMITATIONS SA 160 Markings KIAS Remarks Green Arc 60 130 Normal Operating Range White Arc 51 90 Full Flap Operating Range 2 7 POWER PLANT LIMITATIONS a Number of Engines 1 b Engine Manufacturer Textron Lycoming c Engine Model Number O 320 DZA d Engine Operating Limits 1 Maximum Takeoff Power 119 kW 160 BHP 2 Maximum Engine Speed 2700 RPM 3 Maximum Oil Temperature e Oil Pressure Minimum Oil Pressure Red Line Maximum Oil Pressure Red Line f Fuel Pressure Minimum Pressure Red Line Maximum Pressure Red Line g Fuel grade minimum requirement only aviation fuel h Oil grades minimum requirement h Number of Propellers i Propeller Manufacturer j Propeller Model k Propeller Diameter l Static RPM at Maximum Takeoff Power 2 4 245 F 118 C 25 psi
96. aft Feb 25 2005 11 of 16 SECTION 9 ymphony SUPPLEMENT 1 SA160 SECTION 7 DESCRIPTION AND OPERATION 7 1 GENERAL The information contained in here supersedes the information on the Bendix King KX 125 VHF NAV COM receiver transmitter provided in the Description amp Operation Section of the basic Pilot s Operating Handbookand TC Approved Airplane Flight Manual For a complete description of the GNS 430 system refer to the GARMIN GNS 430 Pilot s Guide P N 190 00140 00 Rev A dated October 1998 or later appropriate revision 7 2 SYSTEM DESCRIPTION The GNS 430 system consists primarily of the GNS 430 unit a GPS antenna a VHF VOR LOC GS antenna and a VHF COMM antenna The GNS 430 unit contains the GPS Receiver the VOR ILS receiver and the VHF Communications Transceiver The unit is mounted in the center of instrument panel in the avionics column The GNS 430 system can be turned ON if the BAT switch and the AVIONICS switch are in the ON position 12 of 16 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 1 Figure 7 1 Front View of the GNS 430 Unit a Key and Knob Functions 1 Left hand Keys and Knobs The COM power volume knob c controls unit power and communications radio volume Press momentarily to enable disable automatic squelch control The VLOC volume knob W controls audio volume for the selected VOR Localizer frequency Press momentarily to enable disable the ident
97. an 3 minutes at maximum RPM Prolonged engine operations below 1000 RPM may cause spark plug fouling Feb 25 2005 4 25 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 i Before Takeoff 4 5i All circumstances for each particular takeoff such as runway surface meteorological conditions etc should be considered With brakes set to avoid fouled spark plugs and battery discharge perform the necessary checks with approx 1000 1200 RPM engine speed Ensure that the seats are fixed and both seat belts are fastened even if no passenger Check that the cabin doors are closed and latched At night adjust instrument and map light intensity corresponding to surrounding light conditions Check the fuel valve is open Turn ON the auxiliary fuel pump to prevent loss of power should the engine driven fuel pump fail during takeoff Ensure the fuel quantity is sufficient for the planned flight Check the mixture is in the FULL RICH position the carburetor heat is OFF and the Ignition switch is in BOTH position Check again that all engine parameters are within the permissible limits Set up the attitude indicator and the compass Adjust the barometric altimeter as required Check the navigation equipment required for planned flight is operational Adjust the trim slightly aft of neutral Set flaps in takeoff position and check visually that they are down NOTE A minimum amount of leaning is permitted for smooth engine oper
98. arburetor heat is activated by pulling aft on the Carburetor Heat control knob This will supply the carburetor with unfiltered preheated air 7 18 Feb 25 2005 gt ymphony SECTION 7 AIRCRAFT SA 160 DESCR amp OPERATION b The VM 1000 Engine Management System NOTE The VM 1000 engine management system and its operation is described subsequently with sufficient information for safe operation of the aircraft Fora more complete description and operation of the VM 1000 System refer to the VM 1000 Supplement at Section 9 Feb 25 2005 7 19 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 VM 1000 Schematic CHT PROBE 1 gt CHT PROBE 2 RPM XDUCER lt MAN PRES XDUCER CHT PROBE 3 lt Oil PRES XDUCER CHT PROBE 4 lt FUEL PRES XDUCER EGT PROBE 2 AMP XDUCER EGT PROBE 3 EGT PROBE 4 gt DATA PROCESSING UNIT FUEL PROBE LEFT FUEL PROBE RIGHT Fuel Indicator TO AUDIO PANEL INPUT VM 1000 Display Figure 7 5 VM 1000 Schematic 7 20 7 17 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 1 Description A data processing unit DPU receives electrical signals generated from different engine sensors The DPU output is connected with the VM 1000 indicator See Fig 7 6 the EC 100 system See Fig 7 7 and when installed with a
99. are versions can be verified on the AUX group sub page 2 SOFTWARE DATABASE VER 2 3 ENROUTE NAVIGATION IFR IFR enroute and terminal navigation predicated upon the GNS 430 s GPS Receiver is prohibited unless the pilot verifies the currency of the data base or verifies each selected waypoint for accuracy by reference to current approved data 2 4 INSTRUMENT APPROACH IFR Instrument approach navigation predicated upon the GNS 430 s GPS Receiver must be accomplished in accordance with approved instrument approach procedures that are retrieved from the GPS equipment data base The GPS equipment database must incorporate the current update cycle a Instrument approaches utilizing the GPS receiver must be conducted in the approach mode and Receiver Autonomous Integrity Monitoring RAIM must be available at the Final Approach Fix b Accomplishment of ILS LOC LOC BC LDA SDE and MLS or any other type of approach nor approved for GPS overlay with the GNS 430 s GPS receiver is not authorized c Use of the GNS 430 VOR ILS receiver to fly approaches not approved for GPS require VOR ILS navigation data to be present on the external indicatore 4 of 16 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 1 d When an alternate airport is required by the applicable operating rules it must be served by an approach based on other than GPS or Loran C navigation the aircraft must have the operational equipment capable of
100. ate Static Source table in Section 5 P5 11 q Spin Recovery Procedure WAV OBE Cds AEP IDLE ATEOS irit e OG wd OW e NEUTRAL 3 Rudder FULL OPPOSITE TO DIRECTION OF ROTATION At the same time 4 Elevator rar ds NEUTRAL 5 Rudder when rotation stops sss NEUTRAL As rotation stops make a smooth recovery from the dive If flaps were extended retract and establish horizontal flight with engine power as required DR 3 10 Feb 25 2005 SECTION 3 gt ymphony EMERGENCY PROCEDURES SA 160 3 7 AMPLIFIED EMERGENCY PROCEDURES Engine Failure During Takeoff Roll Y Checklist 3 5 a If loss of power occurs during takeoff roll the aircraft must be brought to a halt as soon as possible in order to avoid leaving the runway Engine power must be reduced to idle It is recommended that flaps be retracted in order to reduce lift force This increases the rolling friction and therefore decreases the accelerate stop distance If the aircraft goes off the runway damage possible collision with obstacles and even overturning cannot be excluded Seat belts and harnesses must be tight to reduce the possibility of injury 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 fuel supply by moving the Mixture control to the position IDLE CUT OFE Turn off the ALT BAT switch and the ignition switch Engi
101. ation when taking off at high elevation airfields j Takeoff 4 5 j Normal Conditions Normal take offs are accomplished with flaps in 20 position However under difficult wind conditions such as crosswind near at the maximum demonstrated crosswinds a takeoff with flaps up may be advisable 4 26 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES Set the trim as required Move the throttle control fully forward and allow the aircraft to accelerate to 53 KIAS Lift the nose wheel and let the aircraft lift off Accelerate the aircraft in a shallow climb to 65 KIAS and then transfer to climb flight with 65 75 KIAS Slowly retract the flaps at an altitude of at least 50 ft and perform further climbing with 80 KIAS airspeed Short Runway Lower the flaps to takeoff position 20 Set the trim as required Hold the brakes on Move the throttle control fully forward and only upon reaching the full engine power release the brakes After reaching a airspeed of 53 KIAS lift the nose wheel and let the aircraft lift off Accelerate the aircraft in a shallow climb to 65 KIAS and then transfer to climb flight with this speed Once clear of any obstacles slowly retract the flaps at an altitude of at least 50 ft and climb at 80 KIAS airspeed Cross Wind When performing a flap ups take off due to heavy crosswinds the aircraft must be accelerated to 60 kias prior to nose wheel lift off k Climb 4 5 k Once esta
102. avionics package for the basic VFR version of the SA 160 For the SA 160 IFR version the owners should refer to the applicable supplements provided in section 9 a Radio and Intercom 7 52 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION The standard equipment of the SA 160 includes a Bendix King KX 125 VHF NAV COM receiver transmitter and an intercom system The NAV COM receiver transmitter is mounted in the center of the instrument panel over the transponder The intercom control panel isinstalled over the NAV COM radio The NAV COM is for radio communication with ground control or other aircraft In addition data of ground stations can be received and indicated for navigation purposes The connection of the crew headsets to the NAV COM radio is provided and controlled by the intercom system It facilitates external and internal communication of the crew members Fig 7 XX shows the front view of the VHF NAV COM receiver transmitter and the control panel of the intercom 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 protected by the circuit breakers labeled NAV COM and ICS b Transponder The Transponder answers interrogating signals from ground stations and enables the ground station to determine the location and altitude of the aircraft A Bendix King KT 76C
103. aximums encountered i e max CHT max Oil Temp max RPM etc STEP 3 Press BUTTONS again The Flight Data Recorder is shut off The recorder data will automatically shut off in approximately 20 seconds if no button is pressed 4 14 AIR TEMPERATURE SYSTEM OPERATION opt Both Outside Air Temp and Carburetor Air Temp are displayed at the same time in one compact indicator for complete air temperature information ata glance OUTSIDE AIR TEMPERATURE OAT is displayed on the left hand side of the indicator both graphically and digitally in degrees C Most true airspeed indicators have the temperature correction scale calibrated in Degrees C making it easy to enter the temperature directly from the OAT display CARBURETOR AIR TEMP CAT or cabin air temp for injected aircraft is displayed on the right hand side of the indicator both graphically and digitally in degrees C As temperatures increase the graph sizes increase proportionately The full color range marks let you see at a glance if you are in a temperature Feb 25 2005 19 of 27 Symphony IRCRAFT SA160 area conducive to icing The digital displays read outin 1 degree C increments to a maximum of99 C and a minimum of 50 C This is very useful for monitoring small changes in temperatures and for calculating temperature related parameters For new engine installations you can take advantage of the high accuracy and repeatability for analyzing carburetor heat
104. blished into the climb flaps up and A C trimmed Turn OFF the auxiliary fuel pump The best rate of climb speed at maximum weight is 80 KIAS Mean Sea Level The speed decreases one knot per 1000 ft to 75 kts as minimum The best angle of climb speed is 70 KIAS flaps retracted For climbing en route the best rate of climb speed plus 5 10 KIAS is recommended The visibility over the aircraft is therefore increased During the climb the engine parameters are to be checked especially the cylinder head temperature Under very high outside temperatures climb speed can be increased to maximize engine cooling Feb 25 2005 4 27 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 I Cruise 4 5 I Adjust the elevator trim to make flying on long routes easier The cruise speed and the cruise power settings depend on many factors such as altitude air temperature aircraft loading and so on The normal cruising power is 55 75 of the rated horsepower of the engine Airspeeds which may be obtained at various altitudes and power settings can be determined from the performance graphs provided in section 5 A correct mixture setting can significantly reduce fuel consumption For that a Establish desired cruise power and allow engine parameters to stabilize b Press BUTTON 1 at VM 1000 display see Section 7 to activate the Lean EGT Mode CAUTION Never exceed the maximum red line cylinder head temperature limi
105. cess approaches departures and arrivals A closest point to flight plan feature is also available from the flight plan key The procedures key IB allows selecting approaches departures and arrivals from the active flight plan When using a flight plan available procedures for departure and or arrival airport are offered automatically Otherwise the user may select the desired airport then the desired procedure Feb 25 2005 15 of 16 SECTION 9 ymphony SUPPLEMENT 1 SA160 b Screen Areas Map Display COM Window Data NAV Fields Window Map Scale Map Page Present Position Desired Track Figure 7 2 Screen Areas Map Page c NavData Card Slots There are two data card slots on the face of the GNS 430 The Jeppesen NavData card should be inserted in the left most slot The second slotis provided for future options and expansion capabilities Insert the card with the swing arm handle at the bottom and the label facing to left 16 of 16 Feb 25 2005 Symphony SA160 AIRCRAFT Symphony uu Airplane Flight Manual Supplement Model SA 160 SUPPLEMENT 2 GARMIN GNC 420 VHF COMIVIUNICATIONS TRANSCEIVER GPS RECEIVER This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and TC Approved Airplane Flight Manual when the GARMIN GNS 430 navigation system has been installed in accordance with GARMIN Installation Manual 190 00140 02 Rev A or later The Information contained h
106. correspondence with fuel level indicator reading After this replace cap securely 3 Nose Section Check the cowling for damage and correct fitting All quick release fasteners of the cowling must be locked Check the windshield for damage such as cracks and scratches and clean if necessary Check the air inlets for damage and obstructions use only authorized cleaning materials The propeller and the spinner are to be checked for nicks cracks or other defects 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 the oil level with the dipstick It should be no less as 5 liters 5 3 qts Then close the oil filler cap accurately Close the oil access door Check the nose gear strut and the wheel fairing for damage If required remove the wheel chock Check tire for cuts wear and proper inflation 4 Right Wing The wing surface should be clear of ice frost snow or other extraneous substances Open the fuel cap and visually check the fuel level for correspondence with fuel level indicator reading After this replace cap securely Check the wing leading edge with the vortex generators for any damage The end of fuel tank vent line must be free of obstructions Check the wing tip and the navigation strobe lights for mechanical Feb 25 2005 4 19 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 damage The security of attac
107. cs column The transponder antenna is installed on the bottom surface of the fuselage The transponder is connected with the blind encoder which transfers altitude data from the pitot static system r1 2 ag PRESSURE 3 FL 12 Figure 7 1 Front View of the GTX 327 Unit 6 of 8 Feb 25 2005 Symp SA160 phon Y SECTION 9 SUPPLEMENT 4 8 o 6 Feb 25 2005 7 3 KEY AND KNOB FUNCTIONS NOTE For mode selection keys see Section 4 IDENT Pressing the IDENT key activates the Special Position Identification SPI Pulse for 18 seconds identifying the transponder return from others on the air traffic controller s screen The word IDENT will appear in the upper left corner of the display while die IDENT mode is active VFR Sets the transponder code to the pre programmed VFR code selected in Configuration Mode this is set to 1200 at the factory Pressing the VFR key again will restore the previousidentification code FUNC Changes the page shown on the right side of the display Displayed data includes Pressure Altitude Flight Time Count Up timer Count Down timer and may include Contrast and Display Brightness depending on configuration START STOP Starts and stops the Count Up and Count Down timers CRSR Initiates entry of the starting time for the Count Down timer and cancels transponder code entry CLR Resets the Count Up and Count Down timers and cancels the previous keypress during code
108. cted field A ground station by radio should if possible be informed of the decision for precautionary landing and the location It is recommended to make a landing approach from the downwind leg above the field This procedure provides enough time and correction possibilities for a precise approach On final approach the normal speed and flap settings should be taken Perform a landing on an non prepared field any damage possible collision with obstacles or overturn can not be excluded Seat belts and harnesses set up tightly reduce the injury hazard 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 brake the aircraft as soon as possible Stop the engine with mixture control and Ignition Switch Then closing the fuel valve interrupt the fuel supply Ditching gt Checklist 3 5 g During a landing in water tighten seat belts to reduce the risk of injury Brief passenger if any on the opening mechanism of the seat belts before touchdown Unlatch door before touchdown Touchdown on the water surface with minimum possible airspeed and maximum angle of attack Evacuate aircraft inflate life vests and raft when clear of aircraft Engine Fire During Engine Start Checklist 3 5 h Engine fires during engine start are usually the result of over priming In such a case the first effort to extinguish the fire s
109. ction switch on Frequency FREQ Feb 25 2005 3 of 6 SECTION 9 gt ymphony SUPPLEMENT 5 SA 160 c Select the desired frequency using the frequency selector 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 knob is pulled out it adds 0 05 MHz to the frequency and tunes in 0 1 MHz steps 0 05 0 15 0 25 etc Pushing the knob in subtracts 0 05 MHz from the displayed frequency The unit is in FREQ Mode and will display distance and the selected frequency SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in the paperwork delivered with the aircraft 4 of 6 Feb 25 2005 Symphon Y SECTION 9 SA 160 SUPPLEMENT 5 SECTION 7 DESCRIPTION AND OPERATION 7 1 GENERAL For a complete description of the KN 62A refer to the applicable BENDIX KING publications 7 2 SYSTEM DESCRIPTION The DME system consists primarily of the KN 62A unit and the antenna thatis located on the bottom of fuselage below the co pilot s seat The unit has a 7 Segment gas discharge display that is dimmed automatically by a photocell An audio output is provided for use in identifying the DME ground station being received The unit electronically converts to distance the elapsed time required for signals to
110. ctions and maintenance must be completely documented The main component of preflight inspection is an aircraft visual check in accordance with the check list Fig 4 1 I Cabin Inthe cabin first unlock the control stick You should ascertain that a current SA 160 flight manual as well the checklists are on board The instrumentation and the control elements of the cockpit are to be checked for external damage Check the fuel quantity by means of the fuel level indicator All switches inclusive the ignition switch must be OFE Verify the instrument map light dimmer switches are in off position CAUTION GJ When the instrument light dimmer switch is in ON position the annunciator lights Fuel Pump and Flaps in Motion will be dimmed See Section 7 Lights Feb 25 2005 4 17 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 AII circuit breakers are in ON position The throttle control lever should be in the closed position and the mixture in idle cut off While moving control stick check the ailerons and the elevator for free and correct movement Check the trim for freedom of movement and set to neutral The seat position and its locking are to be checked Extend the wing flaps and leave this position for a better view of mechanics 2 Left Wing Bleed fuel from the left wing fuel tank drain into a clear vessel and inspect for water and sediment contamination Drain until water or sedi
111. currency of the data base or verifies each selected waypoint for accuracy by reference to current approved data 2 4 INSTRUMENT APPROACH Instrument approach navigation predicated upon the GNC 420 s GPS Receiver must be accomplished in accordance with approved instrument approach procedures that are retrieved from the GPS equipment data base The GPS equipment database must incorporate the current update cycle a Instrument approaches utilizing the GPS receiver must be conducted in the approach mode and Receiver Autonomous Integrity Monitoring RAIM must be available at the Final Approach Fix b Accomplishment of ILS LOC LOC BC LDA SDE MLS or any others type of approach not approved for GPS overlay with the GNC 420 s GPS reveiver is not authorized 4 of 15 Feb 25 2005 Symphon d SECTION 9 SA160 SUPPLEMENT 2 c When an alternate airport is required by the applicable operating rules it must be served by an approach based on other than GPS or LORAN C navigation the aircraft must have the operational equipment capable of using that navigation aid and the required navigation aid must be operational d VANV information may be utilized for advisory information only Use of VNAV information for Instrument Approach procedures does not guarantee Step Down Fix altitude protection or arrival at approach minimums in normal position to land 2 5 DEFAULT SETTINGS If not previously defined the following default settings mus
112. d COMPONENT TAKEOFF 20 kts aircraft LANDING 17 kts only OPERATING MODE NORMAL CATEGORY FOR FLIGHTS IN VER IFR DAY AND NIGHT CERTIFIED FLIGHTS INTO KNOWN ICING CONDITIONS ARE PROHIBITED FLIGHTS IN HEAVY TURBULENT AIR AND CLOSE TO THUNDERSTORMS ARE PROHIBITED SEE THE LIMITATION SECTION IN THE POH MAXIMUM GROSS WEIGHT 2150 Ibs MAXIMUM LANDING WEIGHT 2042 Ibs MANEUVERING SPEED 116 kts For IFR MAX FLAP EXTENDED SPEED 90 kts MAX DEMONSTRATED CROSSWIND equipped COMPONENT TAKEOFF 20 kts aircraft LANDING 17 kts only Feb 25 2005 2 9 SECTION 2 Symphon Y IRCRAFT LIMITATIONS SA 160 THE AIRCRAFT MUST BE OPERATED IN COMPLIANCE WITH THE PILOT S OPERATING HANDBOOK ACROBATIC MANEUVERS INCLUDING SPINS ARE NOT APPROVED 2 Near oil access door ENGINE OIL ABOVE 16 C 60 F SAE 40 OR SAE 50 1 C 30 F TO 32 C 90 F SAE 40 18 C 0 F TO 21 C 70 F SAE 30 OR SAE 40 BELOW 12 C 10 F SAE 30 USE ONLY OIL THAT COMPLIES WITH APPLICABLE PILOT S OPERATING HANDBOOK 9 3 Left fuselage near the engine cowling Symphony Aircraft Industries Trois Rivieres Qu bec Canada MODEL TYPE CERTIFICATE SA 160 A 229 MANUFACTURED SERIAL NO 0X 200X S XXXX 2 10 Feb 25 2005 Symphon d SECTION 2 SA 160 LIMITATIONS 4 On the left fuselage side below the horizontal stabilizer AIRCRAFT DATA PLATE LOCATED AT FIREWALL THIS SIDE 5 On the door
113. d by the Artex Aircraft Supplies Inc Feb 25 2005 7 57 Symphony SA 160 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE SECTION 8 GROUND HANDLING SERVICING AND MAINTENANCE TABLE OF CONTENTS Page 5 1 Generals scott AA Rad teeter dod Ry D BA 8 3 5 3 Inspection l riodS wa A eee ie liada 8 4 56 5 Preventive Maintenance ss ceret rte diaria 8 4 8 7 Alterations to the Aircraft eterne 8 5 89 Ground Handling isspiss AA aiz eet ted WEJ 8 6 EI Re 8 6 b Parking variando ERR ER IER HERE ta 8 7 c Ted Wisin iio diia 8 8 d Jackie 8 8 e Leveling inocente etie pte denas 8 8 8 11 Z tteg edd 8 9 A Dilo 8 9 OSPEGIAICZUON 2 2 war 8 9 Oil MSN 8 9 Capacity d 8 9 Oil and Oil Filter Change eee 8 9 b Fulanito uteri etit panini tastes iade 8 10 Approved Fuel Grades e meistens 8 10 Gri E M 8 10 8 13 Cleaning and Care cnica 8 11 a Windshield and Windows 8 11 b Exterior SUELACES visto tits 8 12 e Propeller ocn sa 8 13 d ENS iii tdi ida 8 13 El TEE eg eege 8 15 8 14 During Flyable Storage EA 8 16 Feb 25 2005 8 2 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 8 1 GENERAL This section provides recommended procedures for proper ground handling servicing and maintenance of the SA 160 The operator of an aircraft is responsible for ensuring that all ai
114. dbook and TC Approved Airplane Flight Manual when the GARMIN GNS 430 navigation system has been installed in accordance with GARMIN Installation Manual 190 00140 02 Rev A or later The Information contained herein supplements or supersedes the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual only in those areas listed in here For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Approved Dates Transport Canada ised Rub 25 2005 Diada Symphony AIRCRAFT SA160 SECTION 9 SUPPLEMENT 1 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective pages in the Supplement as well as the date of issue or revision Revision Level 0 Original Issue PAGE Title i ii 1of16 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 Feb 25 2005 Date of Issue Feb 25 2005 DATE Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Symphony SECTION 9 IRCRAFT SUPPLEMENT 1 SA160 LIST OF REVISIONS Rev Page WE Na Date No Description ii Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 1
115. del O 320 D2A d Engine Type Four cylinder direct drive horizontally opposed e Rated Power f Rated Speed g Bore h Stroke i Displacement j Compression Ratio Propeller a Number b Propeller Manufacturer c Propeller Model d Number of Blades e Propeller Diameter f Propeller Type Fuel a Fuel b Total Capacity c Total Usable Feb 25 2005 air cooled engine with a float type carburetor 119 kW 160 BHP 2700 RPM 130 175 mm 5 125 in 98 425 mm 3 875 in 5 24 1 319 8 cu in 8 5 1 1 MT propeller MT 186 R 140 3D P 244 3 2 1860 mm 73 2 Wood fixed pitch Approved Fuel Grades AVGAS 100 LL blue 122 1 32 2 U S Gal 1101 29 1 U S Gal 1 5 SECTION 1 gt ymphony GENERAL SA 160 Oil a Oil Specification Aviation Grade Straight Mineral Oil MIL L 6082 and Aviation Grade Ashless Dispersant Oil MIL L 22851 b Oil Viscosity Mean Environment MI L 6082 MIL L 22851 Temperature Ashless Dispersant Above 16 C 60 F SAE 50 SAE 40 or SAE 50 1 C 30 F to 32 C 90 F SAE 40 SAE 40 18 C 0 F to 21 C 70 F SAE 30 SAE 30 or SAE 40 Below 12 C 10 F SAE 20 SAE 30 c Max Oil Capacity 7 61 8 qt d Recommended Oil Quantity 4 7 6 6 1 5 7 qt Maximum Certified Weights a Maximum Ramp Weight 975 kg 2150 Ibs b Maximum Takeoff Weight 975 kg 2150 Ibs c Landing Weight 926 kg 2041 Ibs d Maximum Weight in Baggage Compartment 75 kg
116. digital clock and an OAT CAT indicator See Fig 7 5 The VM 1000 Indicator The VM 1000 Indicator is located on the right section of instrument panel adjacent to the radios Table 7 1 shows the displayed engine parameters the units the full sweep graphic display resolution and the incremental steps of the digital readout Color markings of operating ranges caution ranges and prohibited ranges are described in Section 2 Limitations Graphic Display Digit Display Parameter Unit Resolution Incremental Steps Man Pressure in HG 1 IN HG 0 01 IN HG Engine Speed RPM Proportional 10 RPM Fuel Pressure PSI Proportional 0 1 PSI Oil Pressure PSI Proportional 1 PSI Oil Temperature F Proportional 1 F Voltage V Proportional 0 1V Amperage A Proportional 1A CHT F N A 1 F EGT S N A TF Table 7 1 VM 1000 Display parameters Feb 25 2005 7 21 SECTION 7 Symyhon ZONY DESCR amp OPERATION SA 160 e 1992 VWM2VISIONMICHOSYSTEMSING N y A W 459 T Ye FUELP OILP VOLT TRNA E E E 095 W ge 4 05 490 39 FUEL FLW OILT EGT CHT G t x O 4 5 1 2 3 Button 1 Select EGT Graphic Modes Button 2 Select EGT amp 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 1000 Indicator 7 22 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION The Electronic C
117. dure ertet R 6 2 Weight and Balance Determination Weight and Balance Record unes 6 9 Weight and Balance Determination for Flight 6 9 Weight and Balance Example EE 6 14 Equipment Listin ad Asia 6 15 Fig 6 1 Weight and Balance Data Form sese 6 5 6 2 Markings for Aircraft Longitudinal Leveling 6 6 6 3 Weight and Balance Record s i isseire 6 8 6 4 Weight and Balance Loading bom 6 10 6 5 Loading Graph cese tese aceite metet 6 11 6 6 Moment Arm ninia casei ad 6 12 6 7 Weight and Moment Lmits see 6 13 6 8 Weight and Balance Bxample sss 6 15 Feb 25 2005 6 1 SECTION 6 gt ymphony WEIGHT AND BALANCE SA 160 6 1 GENERAL This section provides information to determine the aircraft weight and center of gravity The performance and flying characteristics of the SA 160 aircraft can only be achieved if it is flown within the approved weight and Center of Gravity C of G envelope In addition flight operation outside of the approved weight and C of G envelope will have a negative impact on the aircraft flight characteristics and representa significant risk to the aircraft and its occupants WARNING ty Itis the responsibility of the pilotin command to ensure the aircraft is loaded properly and operated within the prescribed weight and C of G envelope Operation outside of the authorizedweight and balance limitations could cause an acc
118. e Complete procedures for oil and filter change are described in the SA 160 Maintenance Manual Chapter 12 b Fuel Approved Fuel Grades 100 LL Grade Aviation Fuel Color Blue CAUTION GJ Approved grades aviation fuel only must be used for the SA 160 Capacity Total Fuel 123 1 32 2 U S Gallons Usable Fuel 114 1 29 1 U S Gallons Unusable Fuel 91 3 1 U S Gallons Fora fast and complete refueling of the tanks follow these steps 1 Move aircraft in a designated fuel loading area Feb 25 2005 8 10 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 2 Make sure that the BAT switch is in OFF position 3 Ensure fire fighting equipment is positioned and immediately available 4 Ground the aircraft and filling device as required 5 Place a suitable ladder to achieve easily the fuel filler caps on the top of wings 6 Fuel aircraft Ensure approved grade of aviation fuel is used a Remove the fuel cap and fill left tank to the desired level Install fuel cap b Remove the fuel cap and fill right tank to the desired level Install fuel cap 7 Check correct lock of both fuel filler caps Remove excess fuel from wing area using a cloth 8 Remove ground cables 9 Compare reading of fueled amount on filling device with reading on the fuel indicator in the aircraft Additives The operation of the aircraft with an anti freezing additive is approved
119. e DATE Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Date of Issue Feb 25 2005 PAGE 1 7 1 8 1 9 1 10 1 11 1 12 1 13 1 14 2 1 2 2 2 3 2 4 2 5 2 6 2 7 2 8 2 9 2 10 DATE Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 iii Symphony IRCRAFT LOG OF EFFECTIVE PAGES SA 160 PAGE DATE PAGE DATE 2 11 Feb 25 2005 4 10 Feb 25 2005 2 12 Feb 25 2005 4 11 Feb 25 2005 3 1 Feb 25 2005 4 12 Feb 25 2005 3 2 Feb 25 2005 4 13 Feb 25 2005 3 3 Feb 25 2005 4 14 Feb 25 2005 3 4 Feb 25 2005 4 15 Feb 25 2005 3 5 Feb 25 2005 4 16 Feb 25 2005 3 6 Feb 25 2005 4 17 Feb 25 2005 3 7 Feb 25 2005 4 18 Feb 25 2005 3 8 Feb 25 2005 4 19 Feb 25 2005 3 9 Feb 25 2005 4 20 Feb 25 2005 3 10 Feb 25 2005 4 21 Feb 25 2005 3 11 Feb 25 2005 4 22 Feb 25 2005 3 12 Feb 25 2005 4 23 Feb 25 2005 3 13 Feb 25 2005 4 24 Feb 25 2005 3 14 Feb 25 2005 4 25 Feb 25 2005 3 15 Feb 25 2005 4 26 Feb 25 2005 3 16 Feb 25 2005 4 27 Feb 25 2005 3 17 Feb 25 2005 4 28 Feb 25 2005 3 18 Feb 25 2005 4 29 Feb 25 2005
120. e corresponding checklist paragraph Feb 25 2005 4 3 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 4 3 AIR SPEEDS FOR NORMAL OPERATION The following air speeds are important for the safe operation of the aircraft These air speeds apply to a standard aircraft up to maximum weight and under standard conditions at sea level Performance for a specific aircraft may vary from published values depending upon different condition e g different equipment on the aircraft another engine and other atmospheric factors etc a Best Rate of Climb Speed ssania ada arch AO On 80 KIAS decrease ofone knot per 1000 ft to min 73 KIAS b BestAngle of Climb Speed ernennen 70 KIAS c Final Approach Speed Flaps AUT 65 KIAS d Balked Landing incio cia 65 KIAS e Maximum Turbulent Air Operating Speed 11111 1 130 KIAS UI Max Demonstr Crosswind Velocity Takeoff Ldg 20 17 kts 4 5 NORMAL PROCEDURES CHECKLIST a Preflight Inspection 1 Cabin Control SHCK DO acia UNLOCK POE Checklists ennt az AVAILABLE Electrical S Witches iii dai nd OFF Light Dimmer Switches nin naaa OFF Ignition Switch e eege OFF Circuit BEeakerS5 a noinen ctr te rini at emitida d CHECK IN Tiroteo ada aia CLOSED MINGLE a ia WC IDLE CUT OFF Flight Controls trente trt CHECK FREE Ji SIRO REC PCN UE CHECK SET NEUTRAL 4 4 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES PREFLIGHT INSPECTION
121. e manual is divided into 8 sections and contains data for the pilot that must be available in accordance with the CARs Supplementary specifications of the aircraft manufacturer are also included The handbook is intended to familiarize the pilot with the aircraft operating limits emergency procedures normal procedures and performance The handbook 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 as orientation for flight basic training or as a training manual and it may only be used as the current status for the operation of the Aircraft The handbook is divided into sections which are numbered with Arabic digits Each section is divided by separator sheets for speedy reference The operating limits and the emergency procedures are placed before the normal procedures the performance data and the other sections The section Emergency Procedures is marked witha red tab divider so that this section can be looked up immediately Provision for an extension to the handbook is provided Therefore some paragraph numbers figure numbers position numbers and pages are deliberately omitted and annotated Intentionally left blank 1 4 Feb 25 2005 Symphony AIRCRAFT SECTION 1 SA 160 GENERAL 1 3 TECHNICAL DATA Engine a Number 1 b Engine Manufacturer Textron Lycoming c Engine Mo
122. ed in the licensed weight and balance data in the paperwork delivered with the aircraft SECTION 7 DESCRIPTION AND OPERATION 7 1 SYSTEM DESCRIPTION The parking brake system consists of parking brake valve the parking brake knob on the forward portion of the middle console and brake lines The brake lines from the toe brakes to the main wheel brake calipers are plumped through the parking brake valve With the parking brake Feb 25 2005 3 of 4 SECTION 9 gt ymphony SUPPLEMENT 7 SA160 control knob pushed in check valves are mechanically held open allowing normal brake operation When the knob is pulled out the parking brake valve holds applied brake pressure locking the brakes To set the parking brake first apply brake pressure using the toe brakes and then pull the parking brake knob aft SECTION 8 HANDLING SERVICING AND MAINTENANCE 8 1 GROUND OPERATION a Parking Park the aircraft as follows 1 If possible park the aircraft with the nose into the wind 2 Ensure that the flaps retracted 3 Set parking brake CAUTION GJ Do not set parking brake with overheated brakes or during cold weather when accumulated moisture may freeze the brakes 4 Check that all electrical devices are turned OFF and that the ALT BAT switch is in OFF position 5 Close cabin and baggage doors 4 of 4 Feb 25 2005
123. em will flag and no longer provide GPS based navigational guidance The crew should revert to the GNS 430 VOR ILS receiver or an alternate means of navigation other than the GNS 430 s GPS Receiver c RAIM IS NOT AVAILABLE If that message is displayed in the enroute terminal or initial approach phase of flight continue to navigate using the GPS equipment or revert to an alternate means of navigation other than the GNS 430 s GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the GNS 430 s VOR ILS receiver or another IFR approved navigation system 6 of 16 Feb 25 2005 Symphon Y SECTION 9 IRCRAFT SA160 SUPPLEMENT 1 d RAIM IS NOT AVAILABLE on the Final Approach 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 the system will flag and no longer provide course guidance with approach sensitivity Missed approach course guidance may still be available with 1 nautical mile CDI sensitivity by executing the missed approach e Emergency Frequency of 121 500 MHz In an in flight emergency depressing and holding the Comm transfer button for 2 seconds will select the emergency frequency of 121 500 MHz into the Active frequency window SECTION 4 NORMAL PROCEDURES Normal operating procedu
124. erating transfer aircraft to level flight and then to climbing flight Stabilize at a speed of 65 KIAS Retract flaps slowly upon reaching a safe altitude Feb 25 2005 4 31 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 p After Landing 4 5p Retract flaps Turn OFF the carburetor heat and the auxiliary fuel pump Turn OFF pitot tube heat ifit was in operation Turn OFF the landing light NOTE Unnecessary further electrical equipment may be turned OFF to reduce the discharge of the battery q Engine Shut Down 4 5q Check the flaps are completely retracted Turn OFF all avionics Adjust the throttle to 1000 1200 RPM and pull the mixture control back to IDLE CUT OFE Turn OFF the ignition switch Turn off the strobe light and at night the navigation lights Turn off the instrument and map lights cabin lighting turn on the dome light If the dome light is needed leave the BAT switch on r After Engine Shut Down 4 5 r In the cabin check all electrical equipment is turned OFE Ignition switch and ALT BAT switch must be switched OFE The throttle must be closed and the mixture in the position IDLE CUT OFF The installation of control locks protects against damage in strong wind and preserves the flying control hinges Chocking the main wheels and the installation of tie downs prevents inadvertent run away or turnover of the aircraftin high wind conditions 4 32 Feb 25 2005 Symphon Y SECTION 5 SA 160
125. erein supplements or supersedes the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual only in those areas listed in here For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Dale seinem Approved Transport Canada lp aa Issued Feb 25 2005 Symphony AIRCRAFT SA160 SECTION 9 SUPPLEMENT 2 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective pages in the Supplement as well as the date of issue or revision Revision Level 0 Original Issue PAGE Title i ii 1of15 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 Feb 25 2005 Date of Issue Feb 25 2005 DATE Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Symphony SECTION 9 IRCRAFT SUPPLEMENT 2 SA160 LIST OF REVISIONS Rev Page WE Na Date No Description ii Feb 25 2005 Symphony AIRCRAFT SECTION 9 SA160 SUPPLEMENT 2 SUPPLEMENT 2 TABLE OF CONTENTS SECTION PAGE GENERAL i3 eve ke Rn dere oe are ER 2 of 15 LIMITATIONS w ek e orm EEN Reed eR m 3 of 15 EMERGENCY PROCEDURES 6 of 15
126. essure and oil temperature are displayed continuously in two separate full sweep graphic and digital areas Oil Pressure As oil pressure rises the graph size increases proportionately The full color range marks let you see at a glance how close to red line oil pressure you are The digital display reads out in 1 PSI increments to a maximum of 99 This is very useful for monitoring typical engine oil pressure trends Because of the high accuracy and repeatability of this system the oil pressure can be closely monitored for unusual trends For example if you are cruising in a stabilized condition 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 Oil Pressure Alert A warning alert activates whenever the engines redline is reached The display will flash until this condition is corrected Oil Temperature Oil temperature is displayed both graphically and digitally As oil temperature rises the graph size increases proportionately This is consistent with the oil pressure display and makes it very easy to determine relationships between the two parameters The full color range marks let you see at a glance how close to red line oil temperature you are The digital display reads out in 1 degree Fahrenheit increments to a maximum of 300 degrees This is very useful for monitoring typical 6 of 27 Feb 25 2005 Symphony SA160
127. feeder tank the fuel flows to the fuel shut off valve to the auxiliary fuel pump through fire a wall fitting and to the gascolator Past the gascolator fuel flows through the fuel pump located on the engine rear accessory case to the carburetor located at the bottom of the engine See Fig 7 8 Pull knob before rotating valve Figure 7 10 Fuel Shut Off Valve Feb 25 2005 7 33 SECTION 7 gt ymphony DESCR amp OPERATION SA 160 The fuel shut off valve See Fig 7 10 is located on the center pedestal below the instrument panel The valve has two positions OFF or ON When in the OFF position the valve shuts off the fuel supply to the engine during critical emergencies such as engine fire Before it can it can be rotated to the desired position the valve must be unlocked by pulling the round knob on the center of the valve while initiating the rotation b Fuel Quantity Indication Fuel quantity is measured by two capacitive type fuel level probes one in each tank Fuel quantity is indicated by a fuel quantity indicator located on the instrument panel below the VM 1000 display Figure 7 11 The indicator displays a left and a right digital read out of gallons of fuel remaining in each tank Additionally the left and right 00000000 O E GAL 3 FUEL LEVEL VM Figure 7 11 Fuel Level Indicator 7 34 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR am
128. flow achieving approximately 100 degrees cooler than the last known peak The PEAK DISPLAY MODE see Digital Display Modes can be used to perform this if the system has previously found a lean EGT 4 11 ELECTRICAL MONITORING SYSTEM OPERATION VOLTAGE is displayed both graphically and digitally Full color range marks provide a quick reference for fast analysis of voltage levels As voltage rises the graph size increases proportionately Additionally your system has a built in warning system that flashes the graph when system voltage is out of nominal range either too low or too high 14 of 27 Feb 25 2005 Symphony SA160 AMPERAGE is displayed both graphically and digitally Full color range marks provide a quick reference for fast analysis of amperage levels As amperage rises the graph size increases proportionately The digital readout displays amperage at 1 amp resolution This is useful for troubleshooting The amp system functions as an alternator load meter displaying current flow FROM the alternator TO the aircraft electrical system allowing you to see if a load such as pitot heat is really drawing current when turned on You should see an increase on the amp display when you turn on a load such as pitot heat for example This tells you that the pitot heater is drawing power and is probably OK By verifying that voltage remains the same then it can be assumed that the alternator is supporting the additional
129. ft stall The otherwise conventionally designed empennage contains strakes on the horizontal stabilizer leading edge The control surfaces of the aircraft are operated utilizing cables pulleys and push roads The flaps are operated electrically An elevator trim tab Feb 25 2005 7 5 SECTION 7 gt ymphony DESCR amp OPERATION SA 160 is operated manually All three wheels of the landing gear are equipped with fairings The wheels of the main landing gear have hydraulically actuated disc type brakes The SA 160 is powered by the proven and reliable engine of the manufacturer Textron Lycoming model O 320 D2A with a fixed two bladed propeller The modern design and materials used in this aircraft forms the basis for very good flight characteristics performance secure operation and serviceability Special features such as the strakes and the vortex generators improve the aircraft handling characteristic at the edge of the flight envelope 7 5 AIRFRAME The SA 160 airframe uses well proven 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 a welded high strength 4130 steel tube cage which is enveloped by two non structural fiberglass shell half that run from the cowl split line to the tail cone The engine mount and nose gear strut attach to the front section of the tube ca
130. g Blees RETRACT E dA O OR A A AAA W I AC 80 KIAS Short Field Jr 20 Drake wa i EE A dA tia APPLY WTO Cs za E FULL OPEN When full engine power is available Drake A Oi No hi ai nina RELEASE At a speed of 53 KIAS tentes ROTATE to lift off After lift off accelerate to E ccrte tiet Peoria rad 62 KIAS After an altitude of 50 ft is achieved Wins BLAS ec eae EO A tee bet ier rede RETRACT PIES PCC cas ertet E 80 KIAS k Climb BIAS E HH RETRACTED bon PR ADJUST Best Rate Climb Speed etti 80 KIAS Best Angle Climb Speed sume niis 70 KIAS A x Fuel PUMP r eee tte ee et mee ie tee ee ied OFF Engine l aramelt rs ueccer trie tenter reno CHECK I Cruise MI E REN SET Cruise Power in accordance with the flight planning SET Feb 25 2005 4 13 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 MiXTUFE C ADJUST Engine l arameters eene trt tenerae CHECK Fuel QUAY D eege CHECK CAUTION Prolonged operation with a lean mixture at more than 75 engine power could resultin engine damage m Descent Carburetor HO atico lala tene eec eade AS REQUIRED MIXCUTE E ENRICH AS REQUIRED A c SET E EE AS REQUIRED Cylinder Head Temperature CHECK n Before Landing Seat Belts and Harnesses sss FASTE
131. ge At the upper mid fuselage areas are the wing attachment points and at the bottom the leaf spring steel struts of the main landing gear and the wings struts attachments The fuselage cage ends in the tail cone The fuselage cage carries all the in service loads The welded cage structure also provides an exceptional degree of crash worthiness The wings are typical aluminum skin spar and rib construction They are equipped with fowler flaps and ailerons Aluminum alloys are 7 6 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION exclusively used in the wings flaps and ailerons One piece fore and aft spars are made of extruded aluminum construction to carry bending and torsion loads At the roots they are attached by removable bolts to the fuselage cage Attached to the aft spar are the flap tracks the aileron hinges and the bearings for pulleys and bell cranks The wing strut ties into a reinforced rib beam which spans between fore and aft spars Welded aluminum fuel tanks are fitted into the first main bay at the root of the wings Filler cups vents and drains are provided in each tank Ailerons are actuated via control cables and bell cranks with push rods The ailerons are mass balanced The fowler flaps are actuated by an electric flap actuator that is installed in the left wing structure The tail control surfaces are also of conventional aluminum construction The vertical tail has a vertical stabilizer and
132. ge turn OFF the Alternator by the switch ALT Turn off non essential electrical equipment to decreases the battery discharge In such case all electrical load is being supplied by the battery Terminate flight as soon as practical gt 3 18 Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES Icing Checklist 3 5 n Under certain circumstances usually in cold weather icing conditions may prevail and ice can accumulate on external surfaces of the aircraft The occurrence and the manner of icing depends on the air temperature humidity as well as other atmospherically condition but also on the airspeed of the aircraft At the first sign of icing conditions the area of icing should be left as soonas possible WARNING GJ Icing has a very strong negative effect on the aerodynamic characteristics of the aircraft Stalling speed increases Continued flight in icing conditions is prohibited A change of temperature will occur with a change of altitude The pitot heat reduces the chance of ice accumulation on the pitot tube which could cause wrong indications and failure of the static dynamic system The carburetor is especially at risk because of the rapid absorption of heat from the air by vaporization of the fuel To prevent carburetor icing and an engine power loss switch carburetor heat ON Cabin heating and cabin ventilation prevents icing on the windshield It is advisable to
133. ge wash with a mild non alkaline soap and water solution 5 Rinse thoroughly with clean water and then dry with a soft cloth or chamois 6 Apply regularly a high quality automotive wax for aircraft care in accordance with manufacturer s instructions This will 8 13 Feb 25 2005 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE prevent painted surfaces from oxidizing and will help prevent unpainted surfaces from corroding A heavier coating of wax on the leading surfaces will reduce abrasion problems in these areas c Propeller As a part of every preflight inspection take a look at the complete propeller observing the leading edge for cracks and the trailing edge for possible splitting by stone damage Check for existing and proper PU strip Clean propeller if necessary with any car wash solution or equivalent or at least every 50 hours Remove grease and dirt with acommercial detergent which is suitable for polyurethane lacquers Small scratches and nicks should be protected during routine maintenance with a coating of water resistant lacquer preferably Polyurethane Further instructions for propeller operation servicing and maintenance are contained in the propeller owner s manual furnished with the propeller d Engine Periodic cleaning of engine and engine compartment can be very effective in preventive Maintenance Cleaning Procedures WARNING GJ Do not
134. h Atlantic Minimum Navigation Performance Specification MNPS Airspace in accordance with AC91 49 and AC120 33 2 of 15 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 2 c The systems meets RNP5 airspace BRNAV requirements of AC90 96 and in accordance with AC 20 138 and JAA AMJ 20X2 Leaflet 2 Revision 1 provided itis receiving usable navigation information from the GPSreceiver b Navigation is accomplished using the WGS 84 NAD83 coordinate reference datum Navigation data is based upon use of only the Global Positioning System GPS operated by the United States of Amercia SECTION 2 LIMITATIONS 2 1 GARMIN GNC 420 PILOT S GUIDE The GARMIN GNC 420 Pilot s Guide P N 190 00140 20 Rev A dated July 1999 or later appropriate revision must be immediately available to the flight crew whenever navigation is predicated on the use of the system 2 2 SOFTWARE The GNC 420 must utilize the following or later software versions Sub System Software Version Main 2 08 GPS 2 00 COMM 2 00 Feb 25 2005 3 of 15 SECTION 9 gt ymphony SUPPLEMENT 2 SA160 The Main software version is displayed on the GNC 420 self test page immediately after turn on for5 seconds The remaining system software versions can be verified on the AUX group sub page 2 SOFTWARE DATABASE VER 2 3 ENROUTE NAVIGATION IFR enroute and terminal navigation predicated upon the GNC 420 s GPS Receiver is prohibited unless the pilot verifies the
135. h the tow bar to the vehicle 3 Remove any installed rudder lock 4 Remove wheel chocks 5 Tow aircraft to the desired location Feb 25 2005 8 6 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 CAUTION ________ GJ 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 ensure that the wings are clear of any obstacles while the aircraft is being towed Do not exceed the nose gear turning angle of 90 either side of center or damage to the nose gear or main gear may occur Make sure that the tow bar is proper connected to the vehicle 6 Chock the main wheels fore aft 7 Remove the tow bar from the vehicle and the aircraft b Parking Park the aircraft as follows 1 If possible park the aircraft with the nose into the wind 2 Ensure that the flaps retracted 3 Check that all electrical devices are turned OFF and that the ALT BAT switch is in OFF position 4 Set the parking brake CAUTION _ GJ During cold weather accumulated moisture may freeze the brakes 5 Close cabin and baggage doors 8 7 Feb 25 2005 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE c Tiedown A correct tiedown protects the parked aircraft against damage by gusty or strong winds The ai
136. handle forward into the locked position The door handle is spring loaded to the close position To open the door from inside pull the door handle aft to the open position To open the door from the outside utilize the recessed door handle by pressing onto the round part of the handle pulling the handle outward and then turning it down The doors open fully forward The doors and the baggage compartment can be locked with a key from the outside 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 the windows refer to section 8 of this manual 7 25 ENGINE The aircraft is powered by an air cooled four cylinder direct drive horizontally opposed gasoline engine with wet sump lubrication The engine is a Lycoming Model O 360 D2A and is rated at 119 KW 160HP at 2700 RPM The engine is mounted at four points on a steel tube engine mount via dynafocal mounts The engine is equipped with A single barrel float type carburetor with manual mixture control and an idle cut off on the bottom of the engine a starter motor front lower left a belt driven 70A 28V DC alternator front right a dual ignition system with two magnetos rear a vacuum pump to provide suction for the gyro instruments and a fuel pump mounted on the rear of the engine accessory case Feb 25 2005 7 17 SECTION 7 Symphon Y DESCR amp OPERATION SA
137. he Normal Model by pressing BUTTON 1 again Notice that left and right brackets appear on the sides of the graphs when in Leaning Model Leaning mode is not allowed if a EGT probe was defective at power up A flashing EGT graph indicates that the leanest EGT has been detected DIGITAL DISPLAY MODES The digital display shows the temperatures for each EGT and CHT pair and periodically shows the cylinder number ex El C1 A warning message is shown if a cylinder has reached red line temperature ex h2 for hot cylinder 2 or is being shock cooled ex c3 for cooled cylinder 3 12 of 27 Feb 25 2005 Symphony SA160 AIRCRAFT The default mode at power up is PEAK DISPLAY MODE ex P1 means EGT 1 leaned before any other during leaning mode H3 means CHT 3 is the hottest Select any combination by pressing BUTTON 2 as described below Display Mode Cyl Numbers Probes displayed Cyl 1 Pair El CT EGT1 amp CHT1 Cyl 2 Pair RICH EGT2 amp CHT2 Cyl 3 Pair ES C2 EGT3 CHT3 Cyl 4 Pair EA CZ EGT4 amp CHT4 PeakMode TP H PEAKDISPLAY MODE 4 10 LEANING YOUR ENGINE Our exclusive automatic LEANING MODE makes leaning the engine a simple operation without the need to remember values STEP 1 STABILIZE the aircraft engine temps throttle RPM and insure 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
138. he date of issue or revision Revision Level 0 Original Issue PAGE Title i ii 1of 11 2 of 11 3 of 11 4 of 11 5 of 11 6 of 11 7 of 11 8 of 11 9 of 11 10 of 11 11 of 11 Feb 25 2005 Date of Issue DATE Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Feb 25 2005 Symphony SECTION 9 IRCRAFT SUPPLEMENT 3 SA160 LIST OF REVISIONS Rev Page WE Na Date No Description ii Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 3 SUPPLEMENT 3 TABLE OF CONTENTS SECTION PAGE GENERAL ae E EEN d eB ee ace E 2 of 11 LIMITATIONS 22 2 iem bee ee be 4 of 11 EMERGENCY PROCEDURES 4 of 11 NORMAL PROCEDURES 4 of 11 PERFORMANCE oroa eR ERR RETE 7 of 11 WEIGHT AND BALANCE 7 of 11 DESCRIPTION AND OPERATION 7 of 11 Feb 25 2005 lof 11 SECTION 9 gt ymphony SUPPLEMENT 3 SA160 SECTION 1 GENERAL 1 1 INTRODUCTION The Garmin GMA 340 Audio Panel provides audio amplification audio selection marker beacon control and a voice activated intercom system for the headsets and microphones The system allows audio switching for up to three transceivers COM 1 COM 2 and COM 3 and five receivers NAV 1 NAV 2 ADE DME and MKR A fail safe mode connects the pilot head
139. hecklist and Caution Advisory System EC 100 WARNING ty The EC 100 checklist function may serve as a general guideline for the pilot while accomplishing normal procedures However the pilot must be fully familiar with the normal and emergency procedures provided in Section 3 and Section 4 of this handbook The EC 100 display is incorporated in the upper left instrument panel The system provides four several categories of easily accessed information Engine information such as power number of cylinders etc Normal procedures checklists Alerts and warnings The following lists the normal procedures checklists that may be selected Before Starting Engine Starting Cold Engine Starting Hot Engine Taxiing Run Up Takeoff Normal Conditions Climb Cruise Descent Approach Landing Engine Shut Down Feb 25 2005 7 23 SECTION 7 gt ymphony DESCR amp OPERATION SA 160 WARNING LEFT TANK LOW aO Oe mw AC OY 00000 000000 00000 000000 00000 o M00000000 O 00000 Figure 7 7 EC 100 Display 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 side tone will be momentarily present 7 24 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION
140. hment of the aileron counter weight is to be checked At the wing trailing edge the ailerons and wing flaps as well as its hinges are to be checked for damage and condition the ailerons for smoothness and freedom of operation Bonding straps and static dischargers should be firmly attached and in good condition Verify the 20 flap position color marking on the inboard flap track is present and in good condition The quick release locks of the top deck hatches for the right wing are to be checked for proper lock Next through the quick drain of the right wing fuel tank sump drain fuel into clear cup and check for water and sediment Drain until water or sediment is gone The right main gear strut and wheel fairing is to be checked for damage The tire should be checked for proper inflation and condition 5 Fuselage The fuselage skins are to be checked for damage such as delaminations or tears and the antennae for their integrity and security Check the static ports for obstructions and integrity The empennage should be clear of ice frost snow or other extraneous substances The security of attachment of the horizontal stabilizer and the freedom of movement of the elevator are to be checked The piano type hinges of the elevator show no damage and are secured properly as well as the elevator pushrod The trim tab is in neutral position Check trim tab pushrod Rudder as well as its hinges are to be checked for damage smoothness
141. hould be to Feb 25 2005 3 15 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 attempt an engine start in order to draw the excess fuel back into the induction system If the engine starts with higher 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 OFE opening the throttle turning OFF the fuel valve while cranking the engine If is not possible to extinguish the fire turn OFF the ALT BAT switch use the fire extinguisher evacuate the aircraft Engine Fire In Flight Y Checklist 3 5 i If an engine fire clearly exists shut off the fuel supply to the engine by closing the fuel valve Then stop the engine with the throttle the mixture control and the ignition switch Turn OFF the auxiliary fuel pump In order to avoid smoke reaching the cabin check cabin heatis off If smoke enters the cabin via cabin ventilation close it After information of the corresponding ground station about the situation turn OFF ALT BAT switch Proceed withthe Landing Without Engine Power procedure Checklist 3 5 d Electrical Fire In Flight gt Checklist 3 5 j If smoke and or fumes are experienced in the cabin this may indicate a cable fire the whole electrical system of the aircraft should be switched off to prevent spreading of any fire With the exception of the ignition turn all electrical equipment a
142. ident to occur The following sections provide information on how to determine the aircraft weight and center of gravity for safe aircraft operation Specific information regarding the weight moment arm of installed equipment for the SA 160 can be found in the aircraft equipment list provided with the aircraft technical records at the time of aircraft delivery 6 3 AIRCRAFT WEIGHING PROCEDURE At the time of delivery Symphony Aircraft Industries provides for each aircraft the basic empty weight and center of gravity location This data is provided on the Weight and Balance Data Form shown in Figure 6 1 The removal or addition of equipment will affect the basic empty weight and center of gravity position As such a weight and balance amendment ora new aircraft weight and balance will need to be performed 6 2 Feb 25 2005 Symphony SECTION 6 SA 160 WEIGHT AND BALANCE The following procedure must be followed prior to weighting the aircraft a Preparation 1 Verify the aircraft equipment against the provided equipment list to ensure that the list is complete and that all equipment is installed in its proper location 2 Remove all foreign items from aircraft 3 Defuel aircraft drain all remaining fuel and add the unusable fuel again Refer for the proper procedure in the SA 160 Maintenance Manual Chapter 12 SERVICING 4 Remove excessive dirt or moisture 5 Top up engine oil as required to the ma
143. ient The Chart figure then shows the existing wind conditions The correction for a 14 kts headwind becomes 14 kts 9 kts x 10 15 6 decrease This results in the following takeoff distances corrected for the wind Ground Roll 312 m 1024 ft Total distance to clear a50 ft obstacle 329 m 1316 ft b Cruise The cruising altitude and the winds enroute are determined from route restrictions and meteorological conditions The optimal power setting selection for cruise must be determined based on several factors This includes the closer consideration of the cruise performance data Fig 5 9 range profiles Fig 5 10 and endurance profile charts Fig 5 5 4 Feb 25 2005 ymphony SECTION 5 SA 160 PERFORMANCE 11 The relationship between engine power and range is presented in the range profile chart Accordingly the most economical fuel consumption or the longest range will be achieved at a cruise power of approx 65 at 6000 ft Next the cruise performance table data can be read by using the 65 cruise power determined above and the other given values the following result is obtained True Airspeed 117 kts Fuel Consumption 28 1 h 7 4U S Gal h c Fuel Required 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 Cruise Performance chart Fig 5 9 These values are based on standard ICAO temperatures However they are sufficiently
144. ill be kept current by revisions issued by Symphony Aircraft Industries Revision material will contain information necessary to update the text figures and charts of the present handbook and or add information 1 Incorporating Revisions Revisions must be incorporated as they are issued Revision status is noted on List of Revisions page and Log of Effective Pages table in this section Revisions shall be inserted into the handbookas follows a Always replace pages with revision pages of same page number b Insert additional pages in correct numerical order within each section Feb 25 2005 i Symphony IRCRAFT APPLICABILITY REVISIONS SA 160 2 Identification of Revised Material Revisions additions and deletions will be identified by a vertical black line along the outside of the page opposite only the portion of the printed matter that was changed A line along the outside margin of the page beside the page number indicates that non changed material has a new physical location only The date of the revision is shown on each revised page ii Feb 25 2005 Symp hony AIRCRAFT SA 160 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective pages in the POH as well as the date of issue or revision Revision 0 Origin PAGE Title i ii iii iv v vi vii viii ix x xi 1 1 1 2 1 3 1 4 1 5 1 6 LOG OF EFFECTIVE PAGES Level al Issu
145. ime limited Maximum Continuous Power Highest power setting not limited by time Cruise Climb Power Power recommended for cruise climb Maximum Cruise Power The maximum power setting for which specific values of fuel flow and airspeed are presented d Engine Instruments EGT Indicator Exhaust Gas Temperature Indicator CHT Indicator Cylinder Heat Temperature Indicator e Aircraft Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb to the horizontal distance traversed in the same time interval Feb 25 2005 1 11 SECTION 1 Symphon Y GENERAL SA 160 Demonstrated Crosswind Velocity The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control ofthe Aircraft during takeoff and landing was actually demonstrated during certification tests Accelerate Stop Distance The distance required to accelerate an Aircraft to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the Aircraft to a stop Route Segment A part of a route Each end of that part is identified by 1 a geographical location or 2 a point at which a definite radio fix can be established MEA Minimum enroute IFR altitude f Weight and Balance Reference Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes Station A l
146. ions necessary for the aircraft must be accomplished by authorized and licensed personnel only Prior to performing any preventive maintenance SA 160 Maintenance Manual must be obtained to ensure that proper procedures are followed Please contact your SAI authorized Service Station or the SAI Customer Service Department to obtain a copy of the manual When maintenance is carried out an entry must be made in the appropriate aircraft maintenance records 8 7 ALTERATIONS TO THE AIRCRAFT Prior to any alterations to the aircraft please ensure that airworthiness of the aircraft is not violated WARNING GJ Alterations or repairs to aircraft must only be carried out by licensed personnel 8 5 Feb 25 2005 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE 8 9 GROUND HANDLING a Towing The aircraft may be moved by hand with a tow bar or by a towing vehicle Towing by Tow Bar One person can move the aircraft on a smooth level surface by using a tow bar attached to the nose wheel Helpers can push on the wing struts near their attachments to the fuselage or on the leading edge of the vertical fin CAUTION GJ Do not exert force on the control surfaces the propeller blades or o the propeller spinner Towing with a Vehicle To tow the aircraft with a vehicle you should follow these steps 1 Attach the tow bar to the nose wheel and secure 2 Attac
147. iption ii Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 7 SUPPLEMENT 7 TABLE OF CONTENTS SECTION PAGE GENERAL 20305 64 baw ESSE pu a A 2of4 LIMITATIONS ae a ee ross ea raw sA 2 of 4 EMERGENCY PROCEDURES 2 of 4 NORMAL PROCEDURES 2 of 4 PERFORMANCE 6 5 25 6 4 4 24 28d nie ge oS 3 of 4 WEIGHTANDBALANCE 3 of4 DESCRIPTION AND OPERATION 3 of4 HANDLING SERVICING MAINTENANCE 4 of 4 Feb 25 2005 1 of 4 SECTION 9 gt ymphony SUPPLEMENT 7 SA160 SECTION 1 GENERAL 1 1 INTRODUCTION This aircraft is equipped with a parking brake system for an easier aircraft handling on ground This supplement covers additional instructions for aircraft operation pertaining the parking brake SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES No change SECTION 4 NORMAL PROCEDURES 4 1LANDING a Before Landing Use procedure as outlined in the basic Airplane Flight Manual Additional check the parking brake is released The parking brake control knob must be full in 2 of 4 Feb 25 2005 ymphony SECTION 9 SA160 SUPPLEMENT 7 CAUTION A If landing is made with the parking brake set the brakes will maintain any pressure applied after touchdown SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is includ
148. is ON without further accessories approximately 25 V willbe indicated When the engine is operating and the electrical power supply system is functioning proprely approximately 26 28 V should be indicated 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 either to low or to high the EC 100 will automatically begin to flash the respective warning and a pulsing audio tone will be present indicated 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 either to low or to high the EC 100 will automatically begin to flash the respective warning and a pulsing audio tone will be present Circuit Breakers The circuit breaker panel is located on the extreme right side of the instrument panel See Fig 7 15 Feb 25 2005 7 43 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 OOO 00000000 O O NAV LT 5N A SY LDG LT l QS BAT BUS FLAPS VISION MAP LT ALT FLD MAIN BUS GPS 1 NAV 1 ATG COM2 GPS2 AVIONIC 2 IFR Figure 7 15 Circuit Breaker Panel 7 44 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 7 35 LIGHTS a Interior Lighting The interior lighting of the SA 160 consists of three independe
149. is mechanically transmitted to the respective brake master cylinder to the respective hydraulic brake assembly via hydraulic lines Parking Brake The SA 160 is equipped with a parking brake system The parking brake system consists of a parking brake valve the parking brake control knob on the middle console right to the fuel shut off valve and brake lines The brake lines from the toe brakes to the main wheel brake calipers are plumped through the parking brake valve With the parking brake control knob pushed in the check valves are mechanically held open allowing normal brake operation When the knob is pulled out the parking brake valve holds the applied brake pressure locking the brakes into their current position To set the parking brake first apply brake pressure using the toe brakes and then pull the parking brake knob 7 38 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 7 33 ELECTRICAL SYSTEM The SA 160 is equipped with a 28 volt DC electrical system It is powered by a belt driven alternator and a 24V battery located in the aft fuselage behind the baggage compartment An external power source can be connected The external power receptacle is located on the aft wall of the baggage compartment All electrical systems components are protected by circuit breakers The circuit breaker panel is located on the extreme right side of the instrument panel The electric power distribution to the various
150. is that other functions such as UTC LOC and FLT are available while the stop watch is counting STEP 3 When you want to stop timing simply select STOP and the time is frozen for you to observe and or record COUNT DOWN STOP WATCH FUNCTION STEP 1 First you will pre set your timer by moving the selector to the appropriate SEC seconds MIN minutes and HRS Feb 25 2005 23 of 27 Symphony IRCRAFT SA160 hours and allowing each to increment up to the desired value then quickly moving the selector to the next desired position When this is completed move the selector to STOP to hold the current value If you made a mistake move to the RUN position for afew seconds then set again STEP 2 When you are ready to begin timing move the selector to the RUN position The graph will fill to full scale and the timer will begin counting down The graph now represents the percentage of pre set time remaining This is very handy for an instrument approach or for timing when to switch fuel tanks It relieves you of the chore of noting clock times and calculating minutes remaining etc STEP3 When time expires the entire display flashes alerting you to this fact Move the selector switch to the STOP position to clear the countdown timer mode NOTE You can dear the countdown timer mode any time it is running by moving the switch to the stop position 4 18 INITIAL EC100 SET UP The initial set up of
151. knots GS Ground Speed is the speed relative to the ground IAS Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error IAS values published in this Handbook assume zero instrument error KIAS Indicated Airspeed expressed in knots M Mach Number is the ratio of true airspeed to the speed of the sound TAS True Airspeed is the airspeed of an Aircraft relative to undisturbed air which is the CAS corrected for altitude temperature and compressibility 1 8 Feb 25 2005 ymphony SECTION 1 SA 160 GENERAL VA Vo Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the Aircraft Vix Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Va Mye Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time Vro Maximum Structural Cruising Speed is the speed that should not be exceeded exceptin smooth air and then only with caution Vs Stall Speed or the minimum steady flight speed at which the Aircraft is controllable Vso Stall Speed with flap or the minimum steady flight speed at which the Aircraftis controllable in the landing configuration V Best Angle of Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance V Best Rate of Climb
152. lant during flight The system is comprised of an engine parameters displays VM 1000 advisory display EC 100 a fuel indicator display a digital clock a data processing units and engine sensors The 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 upper section of the left instrument panel section The EC 100 display is located in the upper left instrument panel The system provides four several categories of easily accessed information Engine information such as power number of cylinders etc Normal procedures checklists Alerts and warnings The EC 100 checklist function may serve as a general guideline for the pilot while accomplishing normal procedures However the pilot must be fully familiar with the normal and emergency procedures provided in Section 3 and Section 4 of this handbook 2 of 27 Feb 25 2005 Symphon d SECTION 9 SA160 SUPPLEMENT 6 1 2 Specifications Weight 2 5 Kg 5 5 lbs Power Requirements 20 29 VDC Channels 20 channels depending upon configuration Display Method LED and Liquid Crystal Display Operating Temperature 50 C or 70 C SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES Nochange SECTION 4 NORMAL PROCEDURES OPERATION 4 1 INITIAL SYSTEM SET UP The initial system set up of the VM 1000 for your aircraft has been
153. largeleft knob O is used to tune the megahertz MHz value of the stanby frequency for the COM transceiver The small left knob O is usedto tuned the kilohertz kHz value of the stanby frequency for the COM transceiver 12 of 15 Feb 25 2005 Symphony SECTION 9 SA160 SUPPLEMENT 2 The COM flip flop key is used to swap the active and stanby COM frequencies Press and hold to select emergency channel 121 500 MJZ Therange key allows selecting the desired mape scale Use the up arrow side of the key to zoom out or the down arrow side to zoom in The direct to key allows entering a destination waypoint and establishing a direct course to the selected destination The menu key ED displays a context sensitive options list The options list allows making settings changes which relate to the currently displayed page Theclearkey GB is used to erase information or cancel an entry Press and hold this key to immediately display the Default NAV Page The enter key Bis used to approve an operation or complete data entry Itisalso used to confirm information such as during power on The large right knob EY is used to select between the various Page groups NAV WPT or AUX With the on screen cursor enabled the large right knob allows moving the cursor about the page The small right knob is used to select between the various pages within one of the groups listed above Press this knob momentarily to display the on screen cursor
154. lding it in Simultaneously press BUTTON 3 and REM value will be cleared to zero 4 8 FUEL COMPUTER NORMAL OPERATION MODES Press BUTTON 4 to select the desired fuel computer operating mode The mode is displayed below the permanent words FUEL FLW on the display 10 of 27 Feb 25 2005 Symphony SA160 AIRCRAFT FUEL FLW Fuel Flow is the default mode after powering up This mode displays the fuel Oow in the appropriate Units Per Hour both digitally and graphically The digital section provides 0 1 unit resolution The graphic section provides you with a quick reference of the current fuel flow REM This mode displays the current fuel total remaining in gallons Itis digitally displayed in 0 1 gallon increments This mode is ONLY usable if you have kept the computer s memory updated with fuel information corresponding to the actual aircraft usable fuel and have always had the computer operational when fuel is being burned The graphic display is shut off as it has no relationship to this parameter HRS 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 is digitally displayed in 0 1 hour increments This mode is ONLY usable if you have kept the computer s memory updated with fuel information corresponding to the actual aircraft usable fuel and have always had the computer operational
155. levator is approx in neutral position to reduce the angle of attack to sub critical values When the rotation stops neutralize the rudder and make a smooth recovery from the resulting dive increasing engine power as required If flaps were down retract as soon as rotation is stopped NOTE For spin recovery move the ailerons in neutral position and 3 20 Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES check this by means of control stick position to the panel Different aileron forces cause an incorrect neutral position and may delay the spin recovery The maximum altitude loss for a 1 turn spin is 300 ft 1000 ft may required to accomplishing both the spin recovery and the dive Feb 25 2005 3 21 Symphony AIRCRAFT SECTION 4 SA 160 NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS Page EE 4 3 43 Airspeeds For Normal Operation sess 4 4 Zb Normal Procedures Checklist 5 WE AAAA 4 4 a Preflight Inspection eem tete 4 4 b Before Starting Engine sein sica nicas 4 9 e Starting Engine wa nidad 4 9 d Starting Hot Engine cocinada 4 10 e Engine Start With External Power Source 4 10 Dv Warm Upon AiR mee Eh RUN ee nre 4 10 P HEINE Cere EZR N 4 11 h Ground Check ats ni it W o eene 4 11 1 Before Take O usina GEO A EEEE 4 12 IN 4 12 Normal Conditions oae RO ZO A 4 12 Short A WA A 4 13 I Climb ciini aesen tie ani nana cai 4 13 D C
156. load This is a very handy feature for in flight testing verification of electrical loads and the alternator charging system Additionally your system has a built in warning that flashes the graph and triggers the audio visual annunciator system if installed when the alternator does not produce power for the electrical system This occurs at low amperage levels of approximately less than 2 amps 4 12 AUTOTRACK SYSTEM OPERATION The Autotrack system is a breakthrough in modern engine monitoring technology Designed to reduce the pilot s workload by assisting in the tedious and often overlooked job of monitoring engine parameters for deviations from one minute to the next Autotrack adds a new level of safety to engine management Subtle changes may occur in engine parameters that can precede major problems These changes are often missed by even the most attentive of pilots Autotrack alerts you to these changes allowing you to analyze the situation and take appropriate action Feb 25 2005 15 of 27 Symphon ONY SA160 Refer to FIGURE 6 VM1000 QUICK REFERENCE Fs Gis Sj ono FUELP OLP VOLT ANRA oss 182 E FUELFLW our WHEN TO USE Autotrack Climb Activate during climb to alert you periodically as CHT increases and to a decrease in manifold pressure Cruise Activate during cruise to alert you if any parameter begins to drift from your selected starti
157. m failure To protect the gyroscopes the system has a vacuum relief valve that is attached to the firewall in the cabin that is adjusted so that the vacuum gauge will normally indicate 4 5 5 5 in Hg This is sufficient to operate all gyroscopes within their rated RPM A higher setting will damage the gyroscopes at a lower setting the gyroscopes could provide unreliable information At high altitudes above 12 000 ft and at low engine RPM for example during an approach the vacuum gauge indicates lower vacuum pressure This is normal and should not be construed as a system malfunction or animproperly adjusted vacuum relief valve 7 43 STALL WARNING SYSTEM The aircraft is equipped with a stall warning 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 edge of the left wing and a warning buzzer behind the instrument panel Both are connected by electrical wires As the aircraft approaches a stall the center of pressure on the upper surface of the wings moves much forward towards the leading edge of the wings As a result a micro plate located at the transmitter is deflected upwards A mechanical contact is made thereby sending an electrical signal to the warning buzzer in the cockpit The warning buzzer gives off an alerting tone 7 45 AVIONICS The following provides a description of the
158. mentis gone Both fuel tank sumps should be drained daily prior to the first flight The left main gear strut with wheel fairing is to be checked for damage The tire should be checked for proper inflation and condition Next check the wing surface is clear of ice frost snow or other extraneous substances The quick release locks of the top deck hatches for the left wing are to be checked for proper lock Verify the 20 flap position color marking on the inboard flap track is present and in good condition At the wing trailing edge the wing flaps and ailerons as well as its hinges are to be checked for damage and condition the ailerons for smoothness and freedom of operation Bonding straps and static dischargers should be firmly attached and in good condition The security of attachment of the aileron counter weight is to be checked Check the wing tip and the navigation strobe lights for damage Check the wing leading edge with the vortex generators for any damage With ALT BAT in ON position it is possible to check the general function of the stall warning system by carefully moving upwards the small plate on the transmitter 4 18 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES Check the end of fuel tank vent line for obstructions Remove the cover from the pitot tube and check the pitot pressure hole for integrity and that itis clear of obstructions Open the fuel cap and visually check the fuel level for
159. ncludes it own example 5 2 Feb 25 2005 Symphony AIRCRAFT SA 160 SECTION 5 PERFORMANCE 5 5 FLIGHT PLANNING EXAMPLE The following example uses information from the performance charts to plan a flight Example The following information is used Aircraft Configuration Takeoff Weight Usable Fuel Takeoff Conditions Airfield Pressure Altitude Air Temperature Wind Component Runway Length Cruise Conditions Total Distance Cruise Pressure Altitude Cruise OAT Wind Landing Conditions Airfield PressureAltitude Air Temperature Runway Length Feb 25 2005 975 kg 2150 Ibs 110 1 29 1U S Gal 930 ft 13 C 14 kts Headwind 800 m 2625 ft 280 NM 6000 ft 3 C 20 kts Headwind 2000 ft 11 C 1200 m 3937 ft 5 3 SECTION 5 gt ymphony PERFORMANCE SA 160 a Takeoff For this the chart fig 5 6 Takeoff Distance for short fields is to be used The values shown are based on the normal procedure Takeoff Short Field see Section 4 NORMAL PROCEDURES By means of the appropriate column with the air temperature and the line with corresponding altitude the takeoff distance is found Conservative values can be safely established by reading the chart at the next higher value of altitude or temperature This results in the following Ground Roll 370 m 1214 ft Total distance to clear a50 ft obstacle 475 m 1558 ft The runway length of 2000 ft is therefore suffic
160. nd After rotating the engine six revolutions stop the propeller 60 to 120 from its former position WARNING Before rotating the propeller blades make certain that the ignition switch is OFE 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 engine should be started and run in a safe area The preferred method is to fly the aircraft for 30 minutes For returning to service remove all covers locks etc and give the aircraft a thorough preflight inspection see Section 4 Feb 25 2005 8 18 Symphony SA 160 Symphony Approved Airplane Flight Manual Model SA 160 LOG OF SUPPLEMENTS Installed Nol Title Rev Date LI 1 Garmin GNS 430 VHF Comm March 10 05 Transceiver VOR ILS Receiver GPS Receiver LI 2 Garmin GNC 420 VHF Comm March 10 05 Transceiver GPS Receiver LI 3 Garmin GMA 340 Audio Panel March 10 05 L1 4 Garmin GTX 327 Transponder March 10 05 O 5 Bendix King DME KN 62 A March 10 05 O 6 VM 100 Operation March 10 05 O 7 Parking Brake System March 10 05 Symphony mE Airplane Flight Manual Supplement Model SA 160 SUPPLEMENT 1 GARMIN GNS 430 VHF COMMUNICATIONS TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER This supplement must be inserted into Section 9 of the Pilot s Operating Han
161. nd the ALT BAT switch OFE Turn the cabin heat OFF and close the cabin ventilation to avoid smoke ingress into the cabin After discharging fire extinguisher ascertain that the fire has been extinguished Then ventilate the cabin sufficiently 3 16 Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES WARNING le Residual smoke in the cabin can cause feeling of sickness and of nausea Therefore ventilate cabin fully and make a precautionary emergency landing Pop all circuit breakers and set ALT BAT switch ON Then set circuit breakers one by one for required electrics and to localize a possible short circuit Loss of Oil Pressure Checklist 3 5 k Loss of oil pressure may be either partial or complete A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system of the engine However an oil loss and or defect of the oil pump is also possible In either case a landing should be made as soon as possible to investigate the cause and to prevent engine damage A complete loss of oil pressure indication may be the result of a faulty gauge a total oil pump failure or may signify oil exhaustion Immediately proceed toward the nearest airfield and be prepared for the engine to stop suddenly Avoid unnecessary loads on the engine Flight altitude should be maintained Pay particular attention to the oil temperature Depending on the circumstances
162. ne Failure Immediately After Takeoff Y Checklist 3 5 b In climbing flight without engine power the aircraft will lose airspeed very quickly In order to guarantee further controllability the control stick must be moved forward to establish a glide attitude Avoid obstacles and avoid steep angles of bank WARNING ty At no time should the airspeed decrease below the stalling speed for the configuration setting Note This speed increases by increasing the angle of bank of the aircraft See section 5 Fig 5 5 Stalling Speed Feb 25 2005 3 11 ymphony SECTION 3 SA 160 EMERGENCY PROCEDURES When performing an off field landing damage possible collision with obstacles and even overturning cannot be excluded Seat belts and harnesses must be tight to reduce the possibility of injury In order to reduce the danger of a short circuit and or fire the fuel supply to the engine should cut off and the electrical system turned off Cut off the fuel supply by moving the Mixture control to the position IDLE CUT OFF and the fuel valve to OFE Turn off the ALT BAT switch and the ignition switch Touchdown should be made at the lowest possible airspeed Engine Failure During Flight Restart Procedures gt Checklist 3 5 c Sudden and complete engine power loss is usually the result of fuel flow interruption Power should be restored shortly after fuel flow is restored If power loss occurs at low alti
163. ng BUTTON 1 while in normal mode The entire diamond graph display is temporarily used for precise high resolution leaning A flashing EGT graph indicates that the leanest EGT has been detected The display can be returned to the normal mode by BUTTON 1 again a a o o gt 459 gt gt D gt FUELP El H i 2 gt 1 m A gt lt gt gt i490 390 FUEL FLW Ou EGT CHT O O O O Figure 7 8 Leaning Mode The Electronic Checklist and Caution Advisory System EC 100 With reference to Figure 7 8 to select the desired category press the button to go forward orthe lt button to go backwards When the desired category appears pressthe W button to select itandagain to see further information In the event of an alert or warning pressing any button will cause Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION the EC 100 alarm will be removed for approx 1 5 minutes allowing to access other information In case of an emergency press BOTH the 4 and buttons This will immediately select the emergency checklist category and disable any warning alert messages Use to page through the major checklist topics Press Y button to select desired information To quickly return to the beginning display press both the Y and A buttons until the beginning display appears c New Engine Break In Period The Lyc
164. ng point Descent Activate during descent to alert you to increasing manifold pressure and rising EGT due to a leaning mixture HOW TO USE Autotrack STEP 1 STABILIZE the aircraft Set up your desired power and 16 of 27 Feb 25 2005 Symphony SA160 mixture condition Allow the engine time to stabilize i e engine temps and pressures etc STEP 2 Press BUTTON 3 The Autotrack indicator will activate in the display and the system will begin tracking the engine s performance from this point The Autotrack system is now armed and watching for engine deviation from the point you picked To cancel simply press BUTTON 3 again to extinguish the Autotrack indicator Re arm again at any time NOTE Any important alert condition i e low fuel pressure high CHT etc automatically cancels Autotrack mode Autotrack ALERT INDICATIONS 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 enough a graphic pointer circular sweep displays only will show where the parameter was before the deviation occurred This gives you a chance to evaluate the magnitude of the deviation and take the appropriate action To shut off the alert condition return the parameter to its previous value example adjusting manifold pressure due to a climb or simply press BUTTON 3 to shu
165. ng procedure after approx 2 minutes The oil pressure immediately after starting should at least be 25 psi Otherwise shut down engine At night turn ON the NAV light 4 22 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES d Starting Hot Engine 4 5d Set the brakes and turn on the alternator and the strobe light At night turn on the instrument and map lights They should be switched on to check the engine parameters on the VM 1000 display during start Check the carburetor heat is OFE Open the throttle lever approximately 6 mm 1 4in The MIXTURE lever must be in FULL RICH position After ascertaining that the propeller area is clear of people 6 meters engage the starter by rotating the ignition switch clockwise As soon as the engine fires release ignition switch and move 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 2 minutes The oil pressure immediately after starting should at least be 25 psi Otherwise shut downengine At night turn ON the NAV light e Engine Start With External Power Source 4 5e The voltmeter indication on the VM 1000 display will show the proper connection of the external power source If necessary the external power may be electrical disconnected from aircraft by turning BAT off After the engine has started according to b and c or b and d reduce powe
166. nsor NU Alternator Regulator Alternator VM 1000 BAT Ext P From ALT FIELD Circuit Breaker Ext Power Starter Relay External Power Socket Magneto EET Figure 7 14 1 Electrical Power Distribution Simplified Feb 25 2005 7 41 SECTION 7 Symphony DESCR amp OPERATION SA 160 ALT Switch A H 0 Map Light GX D0 Strobe Lights GA 0 vm 1000 PA Flap Control 0 System 0 Blower Electrical d Fuel Pump L Ignition Switch AVIONIC 2 Main Bus Avionic Bus 2 IFR only O NAV Lights A AVIONIC 1 L D e Landing Light _ 0 Dome Lights 3 m Instrument Lights COM 1 a 0 5 60 NAV 1 8 O Stall Warning System a e m A Pitot Heat 2 IC GPS 1 9 A DC Convenience SL A Transponder Oo q Se Encoder Outlet O Turn Coordinator LG Intercom VFR Figure 7 14 2 Electrical Power Distribution Simplified 7 42 7 39 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION This occurs at low amperage levels of approximately less than 2 amps Voltmeter The voltmeter is integrated in the VM 1000 Engine Management System The voltage supplied to the aircraft electrical system is displayed on the VM 1000 indicator in the lower right area both graphically and digitally See Fig 7 5 If the BAT switch
167. nt lighting systems dome light instrument light and map light Dome Light Two single ceiling mounted incandescent dome lights provides for general illumination of the cabin area during pre flight preparation and after landing Additionally they can be used as an emergency lightin the event the instrument lights fail The dome lights are turned off and on with a rocker type switch located in the row of switches below the flight instruments which is labeled DOME LIGHT Instrument Light The instrument 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 equipment are integrally lighted All other instruments are lighted with standard postlights Four LED spotlights three mounted in the headliner above the seats and one above the heat controls provide additional light for specific instrument panel section and middle console areas The instrument light system is controlled and dimmed through the instrument light dimmer switch labeled INST LT located right side the row of switches below the flight instruments Map Light Two luminescent stripes installed under the glareshield provide Feb 25 2005 7 45 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 overall lighting for the instrument panel In the event of an instrument light failure the map light is sufficient to ligh
168. nte tee oie blad 2 9 Feb 25 2005 2 1 SECTION 2 gt ymphony LIMITATIONS SA 160 2 1 GENERAL This section contains the operating limits approved by the regulatory authority the instrument markings the color coding and the most important placards that are necessary for the safe operation of the aircraft engine systems and the aircraft s standard equipment The Chapter 4 Airworthiness of the SA 160 Maintenance Manual contains the prescribed limitations concerning the maintenance 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 limits for specific systems and equipment are incorporated in section 9 entitled Supplements 2 3 AIRSPEED LIMITATIONS Airspeed KIAS KCAS Mk 162 162 Do not exceed this speed in any operation Maximum Structural Cruising 130 130 Speed V Do not exceed this speed except in smooth air and then only with caution Maneuvering Speed V V at weight 975 kg 2150 Ibs Do not make 116 116 full or abrupt control movements above this speed 2 2 Feb 25 2005 Symphon d SECTION 2 SA 160 LIMITATIONS Airspeed KIAS KCAS Maximum Flap Extended Speed 90 89 Vy Flap setting 20 and 40 Do not exceed this speed with flaps down Stalling Speed V Minimum 60 59 steady flight speed at which the aircraft is controllable Stalling Speed Vso Minimum 51 50 ste
169. nts are standard and arranged around the basic T configuration Those are the airspeed indicator top left the attitude indicator top the altimeter top right the turn coordinator lower left the directional gyro center below and the vertical speed indicator lower right Feb 25 2005 7 11 SECTION 7 DESCR amp OPERATION Symphony IRCRAFT SA 160 1234 Deitz Ju up 00 Q 5 6 7 8 00000 000000 00000 000000 00000 00000 25 27 29 31 24 26 28 30 32 34 41 43 40 I 45 33 35 47 48 1 49 1 Annunciator for Fuel Pump Operation 26 Fuel Pump Switch green 27 Avionik 1 Switch 2 FLAPS IN MOTION Annunciator 28 Avionik 2 Switch IFR yellow 29 Pitot Heat Switch 3 PITOT HT Inop IFR yellow 30 Strobe Light Switch 4 EXT PWR yellow 31 Navigation Light Switch 5 EC 100 Display 32 Landing Light Switch 6 Magnetic Compass 33 Dome Light Switch 7 ELT optional 34 Flap Position Indicator 8 Hour Meter 35 Carburator Heat Control 9 Suction Gauge 36 Throttle 10 Air Speed Indicator 11 Attitude Indicator 12 Altimeter 13 CDI IFR 14 Reserved 15 Avionics 16 VM 1000 Display 17 Alt Static Source Valve IFR 18 Clock 19 Turn Indicator 20 Directional Gyro 21 Vertical Speed 22 CDI optional 23 Clock Switch optional 24 Ignition Switch 25 ALT BAT Ext P Schalter 7 12
170. ocation along the Aircraft fuselage usually given in terms of distance from the reference datum Arm The horizontal distance from the reference datum to the center of gravity C G ofanitem 1 12 Feb 25 2005 ymphony SECTION 1 SA 160 GENERAL Moment The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify balance calculations by reducing the number of digits Center of gravity C G The point at which an Aircraft would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the Aircraft C G Arm The arm obtained by adding the Aircraft s individual moments and dividing the sum by the total weight C G Limits The extreme center of gravity locations within which the Aircraft must be operated ata given weight Usable Fuel Fuel available for flight planning purposes Unusable Fuel Fuel remaining after a run out test has been completed in accordance with governmental regulations Standard Empty Weight Weight of a standard Aircraft including unusable fuel full operating fluids and full oil Basic Empty Weight Standard empty weight plus optional equipment Useful load Difference between take off weight or ramp weight if applicable and basic empty weight Feb 25 2005 1 13 SECTION 1 Symphon Y GENERAL SA 160 Payload Weight ofoccupants cargo and baggage Maximum Ramp Weight Maximum
171. of 27 Feb 25 2005 Symphony SA160 SECTION 7 DESCRIPTION AND OPERATION 7 1 SYSTEM DESCRIPTION Factory installed optional equipment is included in the licensed weight and balance data in the paperwork delivered with the aircraft Feb 25 2005 27 of 27 Symphony uu LBA Approved Airplane Flight Manual Model SYMPHONY SA160 SUPPLEMENT 7 PARKING BRAKE SYSTEM This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and TC Approved Airplane Flight Manual when a parking brake system has been installed The Information contained herein supplements or supersedes the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Date sireci Approved Transport Canada Dy aaa Issued Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 7 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective 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 of4 Feb 25 05 2 of 4 Feb 25 05 3 of 4 Feb 25 05 4 of 4 Feb 25 05 Feb 25 2005 i Symphony SECTION 9 IRCRAFT SUPPLEMENT 7 SA160 LIST OF REVISIONS Rev Page WE Na Date No Descr
172. of 6 PERFORMANCE 5 5 5 25 6 6 4 Rohre rad 4 of 6 WEIGHTANDBALANCE 4 of 6 DESCRIPTION AND OPERATION 5 of 6 Feb 25 2005 lof6 SECTION 9 gt ymphony SUPPLEMENT 5 SA 160 SECTION 1 GENERAL 1 1 INTRODUCTION The KN 62 A is a compact panel mounted 200 channel DME that simultaneously indicates range speed and time to selected station or range and frequency The unit can be channeled manually using the frequency selection knobs or externally from an other in the aircraft installed NAV receiver 1 2 SPECIFICATIONS Weight 1 18 Kg 2 6 lbs Power Requirements 11 33 VDC at 15 W Output Power 100 W Nominal Channels 200 Measuring Method Digitally using Large Scale Integrated circuits Range Accuracy 1 NM or 14 whichever is greater from 0 to 99 9 NM 1 NM from 100 to 389 NM 2 of 6 Feb 25 2005 Symphon Y SECTION 9 SA 160 SUPPLEMENT 5 SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES No change SECTION 4 NORMAL PROCEDURES NOTE The KN 62A is shown in figure 7 1 4 1 POWERING ON THE KN 62A a With BAT and Avionic II switches ON place the ON OFF switch of the unit in ON position NOTE Turn on the unit only after engine start up Also turn unit off prior to engine shut down That will protect the solid state circuitry from short duration high voltage spikes and extend the operational life ofthe unit b Place the 3 position fun
173. oment Me corresponding to the basic aircraft empty weight and C of Gy is given by Me WexCofG This data is provided for each SA 160 at time of delivey Feb 25 2005 6 7 SA 160 Symphony WEIGHT AND BALANCE SECTION 6 LQ 8 LNINON 9309 LHDIAM ALANA A Tol VILYA HSIAHH e a 3 G E No o ls DD Hd i2 VIVA ALANA OISVA sql ur sql sql un un sq sqr un sql 7 INAWOW LHOIHM INANOW WAV IHOIHM LNAWOW Wav LHDIAM up dut n NOIIVOHIGON YO arva IHDIAM ALINA C GAAONAYA daaav ATOLINV HO NOLLAINOSAA DISVd DNINNNA HONVHO LHDIAM LNAINOW OISVA Mo JO LHDIAM ALA DISVA HHAWAN NOLIVALSIDAS AIWAN TVIJAS IHIOW IAVYDUIV souepeg pue JYSEM Suposjjy Jusuudmbq 10 mpnyg ut sasueyD JO AIOJSTH snonuyuop AYOIIY 30NV lIvd ANY LHDI1M 6 8 Symphony SECTION 6 SA 160 WEIGHT AND BALANCE 6 5 WEIGHT AND BALANCE DETERMINATION AND RECORD The basic empty weight and center of gravity location data as provided in the Aircraft Weight Form See Figure 6 1 was determined when the aircraft was delivered at the factory This information can be applied only to the specific aircraft serial number and registration number shown on the form The same values basic empty weight moment and C of G are listed in the first line of the Weight and Balance Record shown in Figure 6 3 Thi
174. oming Engine Operation Manual should be consulted to obtain detailed information regarding the new engine break in period When the engine leaves the Lycoming factory it is usable throughout the entire power spectrum However Pilots should not if at all possible exceed cruise powers of 80 until a total of 50 hours has been accumulated and oil consumption has stabilized Until this time aviation mineral oil MIL L 6082 should be used d Ignition and Starting System Engine ignition is provided by two engine driven magnetos and two spark plugsin each cylinder The right magneto fires the lower right and upper left spark plugs and the left magneto fires the lower left and upper right spark plugs Both magnetos work simultaneously and in such a way guarantee a more complete combustion of the fuel air mixture Ignition and starter operation is controlled by acombined rotary type switch This switch is located on the left side of the instrument panel It has the positions OFF R L BOTH and START During normal engine operation the switch must be placed on the BOTH position and only for magneto checks or for emergency use are the R or L Feb 25 2005 7 27 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 positions used While starting the engine the switch is to be rotated to the spring loaded START position This will activate the starter when ALT BAT switch in the ON position When released the starter engage switch will retu
175. on essential electrical equipment sss OFF 3 Land as soon as practical n Icing Watch for signs of icing conditions immediately leave the region in which the icing occurred If possible change flight altitude o Flap Actuator Drive Failure Flap in Motion light stay on when the flaps are fully retracted or extended 1 FLAPS circuit brea k t wodki OO iiie inen te PULL 2 Land as soon as practical Feb 25 2005 3 9 Symphony SA 160 Symphony SECTION 3 AIRCRAFT SA 160 EMERGENCY PROCEDURES WARNING f Icing has a very strong negative effect on the aerodynamic characteristics of the aircraft Stalling speed increases Continued flightin icing conditions is prohibited L Pitot Heat SWR iae iet Ente n ada ON 2 Carburetor Eleat aua coe eorr ri deter peres rri petas ue ON 3 Cabin Heat Ventilation o oonconicnioniccncnnononnnnonnnnnonnrnnonncnnrnnonacinonos ON Land at the nearest airfield 4 Wind shield Heat iiia cert Denier creta ON With an ice accumulation of 5mm ore more on the wing leading edges perform landing with flaps retracted or in 20 position Airspeed in final approach must be higher corresponding the ice accumulation and the flap position p Static Source Blockage IFR T Alternate Static SOURCE iin rire A A Oi sia OPEN Des Airs pe d retia nike A ZPA dE ADJUST According to the Airspeed Calibration Altern
176. ons elevator and rudder for proper deflection smoothness and 4 24 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES freedom of movement in their entire operating range Avoid holes and rutsin the taxi surface when taxiing over uneven ground Do not operate the engine at high RPM while running up or taxiing over gravel loose stones or any loose material to prevent abrasion and stone damage to the propeller blades h Ground Check 4 5h Set the brake and advance the throttle to 1800 RPM Move Ignition switch to L magneto Position note RPM and switch back to BOTH Move Ignition switch to R magneto position note RPM and switch back to BOTH RPM drop should 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 must be run at500 700 RPM without extreme vibrations Open the throttle smoothly to full throttle The engine should accelerate to maximum RPM without faltering Set 1800 RPM and switch ON carburetor heat Its operation makes itself noticeable through a RPM drop at least of 50 RPM Turn OFF carburetor heat The RPM should adjustitself Check engine parameters on VM 1000 display The oil pressure the oil temperature and the fuel pressure must be within the green ranges CAUTION ____ __ GJ Since the engine is closely cowled for efficient in flight engine cooling do not operate it more th
177. oran C VOR DME TACAN NDB NDB DME RNAV operation within the U S National Airspace System in accordance with AC20 138 b One of the approved sensors for a single or dual GNS 430 installation for North Atlantic Minimum Navigation Performance Specification MNPS Airspace in accordance with AC91 49 and AC120 33 2 of 16 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 1 c The systems meets RNP5 airspace BRNAV requirements of AC90 96 and in accordance with AC 20 138 and JAA AMJ 20X2 Leaflet 2 Revision 1 provided itis receiving usable navigation information from the GPSreceiver b Navigation is accomplished using the WGS 84 NAD83 coordinate reference datum Navigation data is based upon use of only the Global Positioning System GPS operated by the United States of Amercia SECTION 2 LIMITATIONS 2 1 GARMIN GNS 430 PILOT S GUIDE The GARMIN GNS 430 Pilot s Guide P N 190 00140 00 Rev A dated October 1998 or later appropriate revision must be immediately available to the flight crew whenever navigation is predicated on the use ofthe system 2 2 SOFTWARE The GNS 430 must utilize the following or later software versions Sub System Software Version Main 2 00 GPS 2 00 COMM 1 22 VOR LOC 1 25 G S 2 00 Feb 25 2005 3 of 16 SECTION 9 gt ymphony SUPPLEMENT 1 SA160 The Main software version is displayed on the GNS 430 self test page immediately after turn on for5 seconds The remaining system softw
178. orm the pilot when the actuator is in operation If the light remains ON when the flaps are fully extended or retracted that there is likely an actuator problem that needs to be investigated 7 17 LANDING GEAR The aircraft has a fixed tri cycle landing gear All three wheels are equipped with an aerodynamic wheel fairing to reduce drag The main gear struts are cantilever leaf springs which are mounted at the bottom of the fuselage cage Hydraulically actuated disc type brakes are fitted to the inboard side of the main gear wheel The nose gear strut consists of a spring steel tube with a turnable wheel fork Nose gear shock absorption is provided by a rubber disc shock absorber unit mounted on the truss structure of the fore fuselage cage The tire sizes for all three wheels are 5 0 x 5 0 At maximum gross weight a tire pressure of 2 87 bars 41 psi for the nose wheel and 2 5 bars 36 psi for the main wheels is required Feb 25 2005 7 15 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 7 19 BAGGAGE COMPARTMENT The baggage compartment in the SA 160 is located behind the seats A baggage door is provided on the left side of the aircraft just behind the pilot s door During flight the baggage should be properly secured at all time For this purpose four cargo tie downs located on the baggage compartment floorboard and two small cargo nets are provided Maximum weight in the baggage compartment is limited to 165 Ibs 75 kg
179. other feature is the engine hours counter When the engine is off the digital display reads the total accumulated engine hours toa maximum of 5999 9 Engine hours are accumulated any time RPM is greater than 1500 4 of 27 Feb 25 2005 Symphony SA160 RPM Alert A warning alert activates whenever the engines redline is reached The RPM display will flash until this condition is corrected 4 3 MANIFOLD PRESSURE OPERATION The manifold pressure system provides both a full sweep graphic analog display and three place digital display The full sweep graphic display resolution is 1 IN HG The full color range marks provide you with a quick reference to manifold pressure when making fast power changes The digital readout provides you with precise manifold pressure information This allows very precise power settings to be achieved You can for example in stabilized conditions watch for small changes in pressure that can indicate throttle creep or induction problems For new induction system designs or modifications to existing designs this repeatability is extremely valuable to judge the performance of the design or design changes Manifold Pressure Alert A warning alert activates whenever the engines redline is reached typically only for turbocharged engines The display will flash until this condition is corrected Feb 25 2005 5 of 27 Symphony IRCRAFT SA160 4 4 OIL SYSTEM OPERATION Both oil pr
180. p OPERATION displays are also presented graphically to show percentage of fuel remaining for quick reference The indicator red arc shows a low fuel level in the corresponding tank from 0 2 5 gallons When a fuel level of 2 5 gallons and less has been reached in a given tank a Lo will be displayed in the corresponding display area of the fuel indicator and the EC 100 will begin to flash low fuel level warning signal coupled to a pulsing audio warning tone Accurate fuel reading can only be taken in non accelerated level flight c Fuel Venting Adequate fuel tank venting is essential for a continuous fuel supply Blockage of the system will result in decreased fuel flow and a potential engine stoppage Both fuel tanks are vented outboard through vent lines which protrude through the bottom surface of both wings near the wing strut The tanks are interconnected by a vent line from the right fuel tank to the left tank The header tank vent line also connects to the left and right wing tank vent line CAUTION ty Clean and non obstructed fuel vents are essential for an uninterrupted fuel supply d Fuel Drain System The fuel system is equipped with drain valves to provide a means for removing trapped water and for the examination of fuel contamination See Fig 7 12 Each wing fuel tank has a drain valve atits base The wing tank drain valves are located on the underside of wing in the wing root a
181. p System tette tint nne tae 7 14 FAT Landing Gear scettur eege 7 15 7 19 Baggage Compartmenl eerie EA 7 16 721 Seats and Seat Belts rete ettet hetero 7 16 7 23 Doors and Windows issiria sesiis iisi 7 17 do ELE al lidera 7 17 a Engine Controls wazon dO ERAT dr 7 18 b VM 1000 Engine Management Dvstem 7 19 c New Engine Break In Period sse 7 27 d Ignition and Starting System sessirnir 7 27 e Air Induction System e na 7 28 f Librication System entrer ione 7 28 g Cooling Syste eet mte eripe 7 29 M Exhaust AAA 7 29 7 27 Propeller tee O EE ETE E O 7 30 Feb 25 2005 7 1 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 TABLE OF CONTENTS CONTINUED Page TER 7 31 a Fuel Distribution siii nia RA Oc Es 7 31 b Fuel Quantity Indication sssssrsisiisesiiisiosisriiiosssirsisiisritas 7 34 Te Fuel Vent ea don alina ob item ede 7 35 d Fuel Drain System ua AA ARA AAAA 7 35 7 91 Brake System sese dieere rri acacia 7 38 7 33 Electrical System retten tie een err eter tins 7 39 a ALT BAT Switch te eter teniente 7 39 b AVIONICS Geet ai nA ii 7 40 c Indicating and Warning Devices sss 7 40 ESCAS E M 7 45 a Interior Ligh ng e de eerte tete nen 7 45 b Exterior Lighting ntm nnt 7 46 7 37 Ventilating and Heating as aussi woo ada aaa 7 47 7 39 Static and Pitot Pressure System sss 7 48 7 41 Nacu
182. phone and microphone to COM 1 if power is removed or if the Mic Selector switch is turned to the OFF position 1 2 SPECIFICATIONS a General Physical dimensions Length 6 4 Width 6 29 Height 1 3 Power Requirements Supply voltage 11 33 Vdc Operating current 2 2A 13 8V spkr on Temperature range 20 C to 55 C normal operation Altitude 50 000 MSL unpressurized 2 of 11 Feb 25 2005 Symphony SA160 AIRCRAFT SECTION 9 SUPPLEMENT 3 b c d Audio Panel Transceiver inputs Receiver inputs Unswitched inputs Input impedance Input isolation Intercom Volume controls VOX level controls VOX circuits Music inputs stereo Intercom isolation modes Headphone Outputs Output amplifiers Power Frequency response A C radio ICS mic Feb 25 2005 3 5 2 500 ohms 60 dB min 3 pilot copilot passengers 2 pilot copilot passengers 6 one per mic input 2 one input mutable 3 pilot crew all 3 stereo pilot copilot passengers 100 mW per stereo channel each headset into 150 ohms with not more than 5 distortion any normal supply voltage Music 100 Hz to 15 kHz nom 100 Hz to 6 kHz nom Special cabin noise band de emphasis 3 of 11 SECTION 9 gt ymphony SUPPLEMENT 3 SA160 SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES 3 1 ABNORMAL PROCEDURES a Failsafe Operation A failsafe circuit connects
183. r iSe liie sone aie emittere D e m rU ea Het 4 13 m Destinada ed 4 14 n Before Landi g ee eerte 4 14 0 Landing esee terrre e ete mnn 4 15 Normal Conditions iz rtv er oes 4 15 Balked Landing ettet ttti 4 15 p After Landing neret erem itera deerit 4 15 q Engine Shut Down 4 16 r After Engine Shut DOWN eee 4 16 Feb 25 2005 4 1 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 TABLE OF CONTENTS Continued Page 4 7 Amplified Normal Drocedures see 4 17 a Preflight Inspection Lal 4 17 Cabin saw wt W AZ c a eee as 4 17 Left Wii 4 18 Nose DECO EE 4 19 Right Wuesse Z O dan esi 4 19 EE 4 20 b Before Starting Engine 4 5 b sess 4 21 c Starting Cold Engine 4 5c sss 4 22 d Starting Hot Engine Bd 4 23 e Engine Start with External Power Source 4 23 E ere TE ees 4 24 g axung 4 5 Sj aint aan ini o end 4 24 B Ground Check A50 ada aS 4 25 i Before Takeoff bt 4 26 G keet wasza zad idonee 4 26 Normal Conditions tre peers 4 26 Short Kutter 4 27 I9 Climb A 5K irn ten rne teet 4 27 D Cruise 4 5 isse n nei RP EEN 4 28 m Descent EE 4 29 n Before Landing 4 00 see cowe nnt 4 30 0 Landing 4 50 cette a WAG deett 4 31 Normal Conditions rette eerte anis 4 31 Balked Landing sxe e nere tite een 4 31 p After Landing 4 5p neuere 4 32 q Engine Shut Down 4 5Q
184. r to idle and disconnect the external power source from the aircraft by an assistant After removing the external power source increase the engine power to 1000 1200 RPM and check that the ammeter indicates an alternator output Feb 25 2005 4 23 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 CAUTION ty If oil pressure is not indicated or it is too low within 30 seconds after engine start stop the engine and determine the cause NOTE In very cold weather it will take a few seconds longer to get an oil pressure indication NOTE Starter manufacturers recommend limiting cranking periods to 30 seconds with a two minutes rest between cranking periods Longer starting attempts will shorten the life of the starter f Warm up 4 5f Warm up the engine at 1000 1200 RPM Engine is warm for takeoff when throttle can be opened without engine faltering In the meantime turn on required electrical equipment such as the navigation equipment setup if necessary and check for proper functioning Check all engine parameters the volt ammeter as well as the suction gauge readings All circuit breakers must be ON g Taxiing 4 5 g After ascertaining the area in the intended taxi direction is clear increase the engine power slowly Taxi forwards a few feet and apply the brakes to determine their effectiveness While taxiing make slight turns to check the function of the steering Check once more ailer
185. rcraft is to be parked as described in b In addition 1 Immobilize the ailerons and elevator by looping the seat belt around the control stick and pulling it tight 2 Chock the main gear wheels fore and aft 3 Secure tie down ropes to the wing tie down rings and to the tail ring The wing tie down rings are located on each upper end of the wing struts Secure at approximately 45 degree angles to the ground and secure each rope to a ramp tie down point 4 Install a pitot tube cover d Jacking If the aircraft requires jacking for maintenance it may be jacked completely or partially off the ground refer to the SA 160 Maintenance Manual In Chapter 7 the specific procedures and required equipment are provided e Leveling 1 For longitudinal leveling of the aircraft the markings of the waterline may be used These are located at the left side of the fuselage before the empennage see Fig 6 2 Section 6 To this points a suitable level should be placed Deflate the nose tire and or raise the nose strut to properly center the bubble in the level 2 To level the aircraft laterally the cage tube located in the upper cabin area with wing attaching points may be used Deflate the main gear wheels tires differentially Feb 25 2005 8 8 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 8 11 SERVICING a Oil Oil Specification Oil must be conform to the last revision of the Textron
186. rding to how much has been pumped into the tank s You are not required to calculate the new total fuel level after adding fuel as on many other fuel computers This system does it for you Follow the steps below to ADD fuel to the computer referring to FIGURE 6 X VM1000 QUICK REFERENCE ALITOTRACK U UELP op VOLT Hs i 7095 182 4 05 Sep OIRE pa EL FLW No 1490 390 EGT CHT O O O O 1 2 3 4 5 VM 1000 Quick Reference Figure 6 x Feb 25 2005 9 of 27 Symphony IRCRAFT SA160 STEP 1 Press BUTTON 4 until the ADD indicator activates STEP 2 Press BUTTON 3 to add tens and BUTTON 5 to add ones to match the fuel that was pumped into the tank s NOTE To top off the tank s just press BUTTON 3 to run up a number more that your max capacity The system will only add what is needed to fill the computers electronic tank to its max capacity as set up in INITIAL SET UP OF THE FUEL COMPUTER STEP 3 If you made a mistake just leave 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 A and the new fuel will be automatically added to the prior fuel REM total Double check this new total by pressing BUTTON A until the REM fuelis shown NOTE In the event you want to zero the current fuel remaining value press BUTTON A until REM is displayed and continue ho
187. re determined Conservative values can be safely determined by reading the chart at the next higher value of altitude or temperature In such a way the given situation equals Ground Roll 295 m 968 ft Landing distance to clear a50 ft obstacle 725 m 2379 ft Feb 25 2005 5 7 SECTION 5 gt ymphony PERFORMANCE SA 160 5 7 USE OF PERFORMANCE CHARTS Tabulations of performance are presented in increments of temperature altitude and other variables Performance for a given set of conditions may be approximated as follows Takeoff climb and landing Enter tables at next higher increment of altitude temperature weight and at zero wind For cruise Enter tables at next lower increment of temperature altitude and fuel loading and the next higher increment of weight if applicable To obtain exact performance values from tables it is necessary to interpolate between the incremental values TAKEOFF SPEED KIAS ISA 20 C ISA 30 C PRESS WEIGHT TOTAL TO TOTAL TO Ib ALT GROUND CLEAR GROUND CLEAR s LIFT OFF 50 ft ft ROLL 50 ft OBS ROLL 50 ft OBS ft ft ft ft 1329 1690 1411 1788 62 1000 1394 1772 1493 1886 2000 1493 1870 1575 1985 1624 2034 1722 2149 2150 58 Example Given Takeoff Weight 2150 Ibs Air Temperature 40 C Airfield Pressure Altitude 2200 ft Headwind 10 kts Find Takeoff Speed at Lift Off Speed at 50 ft Ground Roll Total
188. rea See Fig 7 13 A drain valve is also located at the lowest point of the fuel system which can be accessed at the bottom of the fuselage In Feb 25 2005 7 35 SECTION 7 gt ymphony DESCR amp OPERATION SA 160 addition the gascolator located on the lower left front of the firewall has also a drain which is accessible from 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 contamination Fuel contamination check can be done by using a sampler cup Make sure that enough fuel has been drained to ensure that all water and sediment has been removed Figure 7 11 Drain Valves 7 36 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION Right Wing gt Figure 7 13 Drain Valves on the base of the wing fuel tanks Feb 25 2005 7 37 SECTION 7 gt ymphony DESCR amp OPERATION SA 160 7 31 BRAKE SYSTEM The brake system of the SA 160 comprises of single disc hydraulically actuated brakes on each main landing gear wheel 4 master cylinders located immediately behind the 4 rudder pedals a brake fluid reservoir on the left cabin wall near the fire wall and brake fluid lines and hoses The brakes are operated by pushing the upper part of either the left or right rudder pedal at each pilot position Each set of rudder pedals is interconnected The applied pressure
189. red with the aircraft SECTION 7 DESCRIPTION AND OPERATION 7 1 GENERAL The information contained herein supersedes the information on the intercom system provided in the Description amp Operation Section of the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual For a complete description of the GMA 340 Audio Panel refer to the GARMIN GMA 340 Audio Panel Pilot s Guide P N 190 00149 10 Rev A or later appropriate revision Feb 25 2005 7 of 11 SECTION 9 gt ymphony SUPPLEMENT 3 SA160 7 2 SYSTEM DESCRIPTION The GMA 340 intercom system consists primarily of the GMA 340 audio control unit located on the instrument panel center high the pilot and Co pilot audio jacks mounted on the middle console and the Push To Talk switches located on the control sticks r MKR BCN y COM 1 NAV GMA 340 Ea MKR cont coma cons O 3 NAV2 Sel el test CABIN AUDIO ICS ISOLATION oW Jj COPILOT L ICS MIC MIC GD mm mmm LO COM1 COM2 COM3 Sep MIC 112 A dcs Figure 7 1 Front View of the GMA 340 Unit 7 3 KEY AND KNOB FUNCTIONS The left small knob Q controls ON OFF function ARM Marker Beacon Lamps MKR ue Marker Beacon Receiver Audio Select Mute Button E a 8 of 11 Feb 25 2005 Symphony AIRCRAFT SECTION 9 SA160 SUPPLEMENT 3 MKR Marker Beacon Receiver Sensitivity Indicator LEDs s Marker Beacon
190. res are completely described in the GARMIN GNS 430 Pilot s Guide P N 190 00140 00 Rev A dated October 1998 or later appropriate revision NOTE The GNS 430 is shown in figure 7 1 Feb 25 2005 7 of 16 Symphony IRCRAFT SA160 4 1 POWERING ON THE GNS 430 a Rotate the Com power volume knob c clockwise to turn the unit on and set the desired radio volume b A welcome page appears briefly and the unit will conduct a self test to ensure proper operation c Once the self test concludes the database confirmation page is displayed showing the effective and expiration dates of the Jeppesen database on the NavData card Press ggg to acknowledge the database page and proceed to the instrument panel self test page d The instrument panel self test page allows you to verify that the GNS 430 is communicating properly with in panel instruments Compare on screen indications with the information depicted on connected instruments such as the CDI HIS RMI and or external annunciators Once you have verified proper operation press EMB to display the Satellite Status Page e Rotate the smallrightknob Group to select the desired page in the NAV 8 of 16 Feb 25 2005 Symphony SA160 4 2 FREQUENCY SELECTION a If the tuning cursor is not currently in the desired window COM or VLOC press the small left knob momentarily b Rotate the large left knob to select the desired megahertz MHz value n
191. rgency situation arise These procedures are offered as a course of action for coping witha given situation or condition They are not a substitute for sound judgment good airmanship and common sense Standard Emergency Procedures are a part of pilot training The information given here does not replace this education They provide a source of reference for the procedures that are applicable to this aircraft 3 3 AIRSPEEDS FOR EMERGENCY OPERATIONS a Stalling Speeds 975 kg 2150 1bs Flaps UP ur oi ROR tette 60 KIAS 975 kg 2150 Ibs Flaps Full Down 51 KIAS b Maneuvering Speeds 975 KS 2150108 oi AO AG Ao a 116 KIAS c Never Exceed Speed ue 162 KIAS d Speed For Maximum Gliding Distance Without Engine Power D Flaps Pie waze ta 74 KIAS AA A RE A i eren eee 65 KIAS Gliding at the above speeds will result in 1 6 NM of gliding distance per 1000 ft for both flight configurations Feb 25 2005 3 3 SECTION 3 Symphon Y EMERGENCY PROCEDURES SA 160 3 5 EMERGENCY PROCEDURES CHECKLIST a Engine Failure During Takeoff Roll dl TACONES loteria IDLE 2 Apply brakes and hold direction Avoid obstructions if possible 3 NAPS zy RETRACT 4 MIXEUTG andanada IDLE CUT OFF 5 Ignition Switch nowe aaa OFF ee WE DN E OFF b Engine Failure Immediately After Takeoff 1 9g m a Establish glide Airspeed with Flaps down sss 65 KIAS Airspeed with Flaps Up ad 74 KIA
192. rn automatically to the BOTH position To provide an easier starting in cold weather conditions the aircraft is equipped with an engine priming system The system consists off one primer pump and three priming nozzles on the cylinders No 1 2 and 4 The manually driven primer pump is installed on the middle console left to the fuel shut off valve The fuel priming nozzles inject the fuel direct in front of the cylinder intake valves e Air Induction System Carburetor induction air enters through an air intake on the right side of the lower cowling and is carried through a wet air filter an alternate air door and ducts to the carburetor air box Should the air induction filter become blocked or when the carburetor heat is in the ON position the engine will draw unfiltered preheated air from the area around the exhaust pipe inside the lower cowl CAUTION __ __ GJ When the carburetor heat switched ON the heated air is sucked in without filtering Therefore the carburetor heat should always be turned off on the ground f The Lubrication System The engine has a fully pressurized wet sump lubrication system Aviation grade oil serves as lubricant with the correct viscosity recommended by the engine manufacturer depending on the conditions for use For engine oil grade and specifications refer to Section 8 HANDLING AND MAINTENANCE 7 28 Symphony SECTION 7 SA 160 DESCR amp OPERATION The capacit
193. rworthiness directives are complied with and that the handling servicing and maintenance of the aircraft is done when required and in accordance with the appropriate Aviation Regulations The following information will help you to keep your aircraft in the best mechanical and airworthy condition 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 abreast of the newest information on the management of this aircraft Any correspondence regarding your aircraft should include the aircraft serial number to ensure proper response The Serial Number can be found on the Identification Plate located on the lower part of the left forward doorpost The SA 160 Maintenance Manual Illustrated Parts Catalog and their revisions are available from Symphony Aircraft Industries Inc Customer Service Department 8 3 Feb 25 2005 Symphony SECTION 8 SA 160 GROUND HANDLING SERVICING amp MAINTENANCE 8 3 INSPECTION PERIODS Symphony Aircraft Industries Inc has developed an Inspection Time Interval Chart for the SA 160 This chart provided by SAI recommends inspection items and time intervals e g 50 100 200 hours Inspections requirements are provided in the SA 160 Maintenance Manual Chapter 5 As required by the airworthiness regulations all civil aircraft must undergo a complete inspection each twelve calendar mon
194. s of Figure 6 7 Hence one can find that it lies in the permissible range and therefore the planned loading is permissible 6 14 Feb 25 2005 Symphony AIRCRAFT SA 160 WARNING GJ The data provided in Figure 6 7 is provided in both inches pounds and in meters kilograms One should ensure that consistent units are used throughout the calculation WEIGHT ARM MOMENT Ibs in in Ibs 100 Basic Empty Weight 1470 98 6 1449 32 Pilot and Passenger 385 101 2 389 62 Fuel 30 1 Gallons Usable 120 107 4 128 08 Baggage 1 60 122 8 73 68 Baggage 2 40 159 1 63 64 Ramp Weight 2075 101 45 2105 14 Fuel for Engine Start Taxi and Runup 8 8 107 4 9 45 Total Loaded Aircraft 2066 2 101 42 2095 65 Figure 6 8 6 9 EQUIPMENT LIST The equipment list applicable to a particular aircraft serial number is included in the Serialized Equipment List is provided with the aircraft Technical Log at delivery Feb 25 2005 6 15 Symphony SA 160 Symphony SECTION 7 SA 160 DESCR amp OPERATION SECTION 7 DESCRIPTION AND OPERATION OF THE AIRCRAFT AND ITS SYSTEMS TABLE OF CONTENTS Page TL Generali naraenia caian 7 5 7 9 Airera tssiri ia teet io eid d datei drea 7 5 LO Afra a A CWA e dd A dir fa 7 6 7 77 Flight Controls ostia ie AI wi tha iride 7 7 7 9 Instrument Panel isis ina 7 11 7 11 Flight Instruments irte trente ce 7 11 7 13 Ground Control E 7 14 7 15 Wing Fla
195. s below the door handle Rescue SENO PUSH AND TURN eS DOWN TO OPEN 6 On the baggage door 99 LBS MAXIMUM BAGGAGE FORWARD OF RED MARKING 99 LBS MAXIMUM BAGGAGE AFT OF RED MARKING MAXIMUM 165 LBS COMBINED SEE WEIGHT AND BALANCE DATA Feb 25 2005 2 11 SECTION 2 LIMITATIONS Symphony IRCRAFT SA 160 7 Near external power receptacle CAUTION THIS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND A NEGATIVE GROUND SYSTEM OBSERVE PROPER POLARITY REVERSE POLARITY WILL DAMAGE ELECTRICAL COMPONENTS 24 VOLTS D C 8 Near fuel tank filler cap AVGAS ONLY CAP GRADE 15 US GAL 100 LL 57 Liters AVGAS ONLY CAP GRADE 57 LITERS 100LL 15 U S GAL 2 12 For aircraft registered in countries where imperial units are used For aircraft registered in countries where SI units are used Feb 25 2005 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Page 3 1 General epe aaa 3 2 3 3 Airspeeds for Emergency Operation 3 3 3 5 Emergency Procedures Checklist ee 3 4 a Engine Failure During Takeoff Roll 3 4 b Engine Failure Immediately After Takeoff 3 4 c Engine Failure During Flight Restart Procedures 3 4 d Landing Without Engine Power 3 5 e Rough Engine Operation sse 3 5 f Precautionary Landing With Engine Power
196. s form is provided to track the current status of the aircraft basic empty weight after the addition of new equipment or aircraft modifications 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 affects weight or moment and is used to amend the basis empty weight and balance data 6 7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT The following procedure will enable the determination of the aircraft weight and C of G position for flight operation The results obtained must be compared with the authorized weight and C of G envelope to ensure that the aircraft operation is within the prescribed limits It is recommended that the SA 160 Weight and Balance Loading Form provided as Figure 6 4 be used to perform the calculation a Enter the weight of all items to be loaded in the weights and balance loading form of Figure 6 4 and add each item to the basic empty weight Write the aircrafttotal weightatthe bottom ofthe table Feb 25 2005 6 9 SECTION 6 gt ymphony WEIGHT AND BALANCE SA 160 b Determine the moment of all items to be carried by using the graph provided as Figure 6 5 or by multiplying the weight of each item by the moment arms provided in Figure 6 6 Enter the arm and moment data into the loading form Add all resulting moment arm for each item to the empty weight moment Write the aircraf
197. selection 8 Reduces Contrast and Display Brightness when the respective pages are displayed Also enters the number eight into the Count Down timer 7 of 8 SECTION 9 gt ymphony SUPPLEMENT 4 SA160 Es 9 Increases Contrast and Display Brightness when the respective pages are displayed Also enters the number nine into the Count Down timer 7 4 ALTITUDE TREND INDICATOR When the PRESSURE ALI page is displayed an arrow may be displayed to the right of the altitude indicating that the altitude is increasing or decreasing Of two sizes of arrows may be displayed depending on the rate of climb descent The sensitivity of these arrows is set using the GTX 327 Configuration Mode 7 5 AUTOMATIC ALT STBY MODE SWITCHING The GTX 327 is configured for automatic standby switching The mode will automatically change to ALT when the aircraft has become airborne Also the mode will change to STBY automatically when the aircraft has touched down The signal for that switching the GTX 327 receives from the GPS unit depending on aircraft speed Additionally a delay time can be set in the Configuration Mode causing the GTX 327 to wait a specified length of time after landing before automatically changing to STBY mode 8 of 8 Apr 02 2002 ymphony SECTION 9 SA160 SUPPLEMENT 4 SECTION 9 Symphon Y SUPPLEMENT 4 SA160 Symphony IRCRAFT Approved Airplane Flight Manual Model SYMPHONY SA160 SUPPLEMENT 5 BENDIX
198. t Always return the mixture to full rich before increasing power settings Prolonged operation with a lean mixture at more than 75 engine power can result in engine damage Avoid rough engine operation c Smoothly lean engine mixture by rotating the knob counter clockwise to start the EGT bars climbing about one bar per 2 seconds If the leanest EGT has been detected the bar graph for that EGT will begin flashing Stop leaning d Enrich engine mixture by rotating mixture knob counter clockwise to set final mixture as follows 1 For Maximum Power Cruise up to 75 power 150 F on rich side peak EGT 4 28 Feb 25 2005 ymphony SECTION 4 SA 160 NORMAL PROCEDURES 2 For Best Economy Cruise 75 power and below Operate at peak EGT or enrich to obtain engine smoothness For further information refer to Lycoming Operator s manual and VM 1000 Manual While cruising check the engine parameters on VM 1000 display frequently Keep track of fuel status in terms of flight time and fuel burn per hour as well as by indications of fuel level indicators m Descent 4 5 m Before descent turn ON the carburetor heat or set according to atmospheric conditions if CAT indicator is installed check reading and enrich the mixture as required While performing a power off descent in order to check the power response and prevent plug fouling periodically partially open and then close the throttle When leveling off set
199. t airports to display a window listing up to d Continue rotating the small right knob airport to highlight the desired e Press EB to accept the selected waypoint s identifier and press ENT a second time with Activate highlighted to begin navigating to the selected waypoint 10 of 16 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 1 4 7 GNS 430 INTEGRATION The GNS 430 system is integrated into the aircraft avionics installation in two configurations a Single GNS 430 GPS 1 interfaced with the CDI VOR LOC ILS GS Indicator and a 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 LOC Indicator 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 indicated by illumination of the GPS or VLOC annunciation in the lower left corner of the GNS 430 display When VLOC is selected for display the CDI displays course deviation from a VOR Localizer LOC or Glideslope G S and GPS truck deviation when GPS is selected SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance datain the paperwork delivered with the aircr
200. t all the instruments and controls required for safe flight and landing by night The map light system is controlled and dimmed through the instrument light dimmer switch labeled MAP LIGHT located right side the row of switches below the flight instruments Day Night Function for Advisory Lights When the instrument light system is turned on the brightness of the Fuel Pump Pitot HEAT and Flaps in Motion annunciator lights will be simultaneously reduced CAUTION 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 during the day b Exterior Lighting The aircraft has a combined navigation strobe lights on each wing tip as well as a landing light installed on the left side of the lower engine cowling The exterior light control switches are located on the lower section of the leftinstrument panel in front of the first pilot To activate the navigation lights strobe light and landing light the respective switches must be placed in the ON position 7 46 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION 7 37 VENTILATION AND HEATING To supply fresh air into the cabin two adjustable air nozzles are provided They are located on the forward left and right cabin sidewall areas just below the instrument panel Ram air is provided to the air nozzles using air intake located on each side
201. t be made in the SET UP 1 menu of the GNC 420 prior to operation refer to Pilot s Guide for procedure if necessary a dis spd nm kts sets navigation units to nautical miles and knots b alt Vv ft fpm sets altitude units to feet and feet per minute c map datum WGS 84 sets map datum to WGS 84 see note below d posn deg min sets navigation grid units to decimal minutes Note In some areas 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 GNC 420 prior to its use for navigation Feb 25 2005 5 of 15 SECTION 9 gt ymphony SUPPLEMENT 2 SA160 SECTION 3 EMERGENCY PROCEDURES 3 1 ABNORMAL PROCEDURES IFR a Missing or Invalid Navigation Information If GARMIN GNC 420 navigation information is not available or invalid utilize remaining operational navigation equipment as required b RAIM POSITION WARNING If that message is displayed the system will flag and no longer provide GPS based navigational guidance The crew should revert to an alternate means of navigation other than the GNC 420 s GPS Receiver c RAIM IS NOT AVAILABLE If that message is displayed continue to navigate using the GPS equipment or revert to an alternate means of navigation other than the GNC 420 s GPS receiver appropriate to the route and phase of flight
202. t off the AUTOTRACK system If optionally equipped an audible and visual alert will activate in the EC100 caution advisory system Feb 25 2005 17 of 27 Symphon ZONY SA160 4 13 FLIGHT DATA RECORDER SYSTEM OPERATION The Flight Data Recorder System comes standard with your VM 1000 and is designed to allow you to review and record the performance of the engine and systems during each flight This is extremely valuable during initial Right testing and for subsequent trend analysis 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 period of time Minimum and maximum values are automatically recorded during the flight and can be reviewed at any time before the next flight Taxi data is automatically omitted as this info is generally not important Actual time of flight is also recorded Refer to FIGURE 7 VM1000 QUICK REFERENCE AN Gis Yes FUELP OLP VOLT e oss 1 182 E AO safe Rei four EGT CHT OO 0 0 0 3 4 5 18 of 27 Feb 25 2005 Symphony SA160 HOW TO USE Flight Data Recorder STEP Press BUTTONS The first set of data are flight minimums encountered i e lowest fuel pressure lowest voltage amperage etc Also the RPM digital display now shows the actual flight hours and tenths STEP 2 Press BUTTON 5 again The next set of data are flight m
203. t total moment at the bottom of the table c Divide the total moment by the total weight to determine the aircraft new CofG location d In a and c plot the weight and C of G values on the graph Weight and Moment Limits provided as Figure 6 7 to ensure that the point falls within the envelope and the intended weight and C of G loading is permissible WEIGHT AND BALANCE LOADING FORM WEIGHT ARM MOMENT Ibs in in Ibs 100 Basic Empty Weight Pilot and Passenger Fuel Usable Baggage 1 Baggage 2 Ramp Weight Fuel for Engine Start Taxi and Runup Total Loaded Aircraft T Figure 6 4 6 10 Feb 25 2005 Symphony SECTION 6 SA 160 WEIGHT AND BALANCE LOADING GRAPH 525 500 475 450 425 400 375 PILOT AND PASSENGER 350 325 300 275 250 225 200 FUEL LOADING WEIGHT Ibs 175 150 125 m BAGGAGE AREA 1 75 E 50 25 BAGGAGE AREA 2 0 50 100 150 200 250 300 350 400 450 500 MOMENT 100 in lbs Figure 6 5 Feb 25 2005 6 11 SECTION 6 gt ymphony WEIGHT AND BALANCE SA 160 MOMENT ARM ITEM MOMENT ARM in Pilot Passenger Baggage 1 Baggage 2 Fuel Usable Figure 6 6 6 12 Feb 25 2005 Symphon
204. tation Distance RMT FREQ GS T KN 62A TSO BENDIX KING Figure 7 1 Front View of the KN 62A Unit 6 of 6 Feb 25 2005 Symphony SA 160 Symphony SA 160 Symphony AIRCRAFT Airplane Flight Manual Supplement Model SA 160 SUPPLEMENT 6 VM 1000 Electronic power Plant Instrumentation This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and TC Approved Airplane Flight Manual when VM 1000 Electronic Power Plant Instrumentation has been installed into the SA 160 using the Vision Microsystem Inc VM 1000 Installation Manual P N 5010012A dated 2001 The Information contained herein supplements the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual Date 4 rect Approved Transport Canada lp aa Issued Feb 25 2005 Symphony SA160 SECTION 9 SUPPLEMENT 6 LOG OF EFFECTIVE PAGES The following Log of Effective Pages provides a listing of all effective pages in the Supplement as well as the date of issue or revision Revision Level 0 Original Issue PAGE Title i ii 1 of 27 2 of 27 3 of 27 4 of 27 5 of 27 6 of 27 7 of 27 8 of 27 9 of 27 10 of 27 11 of 27 12 of 27 13 of 27 14 of 27 15 of 27 Feb 25 20
205. that provide 4 096 active identification codes Pushing one of these keys begins the code selection sequence The new code will not be activated until the fourth digit is 4 of 8 Feb 25 2005 Symphon d SECTION 9 SA160 SUPPLEMENT 4 entered Pressing the CLR key will move the cursor 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 previous code The numbers 8 and 9 are not used for code entry only for entering a Count Down time and in the Configuration Mode SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in the paperwork delivered with the aircraft SECTION 7 DESCRIPTION AND OPERATION 7 1 GENERAL The information contained herein supersedes the information on the BENDIX KING KT 76 A Transponder provided in the Description amp Operation Section of the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual Feb 25 2005 5 of 8 SECTION 9 gt ymphony SUPPLEMENT 4 SA160 For a complete description of the GTX 327 Mode A C Transponder refer to the GARMIN GTX 327 Mode A C Transponder Pilot s Guide P N 190 00187 00 Rev A or later appropriate revision 7 2 SYSTEM DESCRIPTION The GTX 327 unit is located on the instrument panel in the avioni
206. the straight up position as before The display will read LOC rdy Wait for this message to disappear then move the selector to any desired position You can now check LOC for the correct local time NOTE Since universal and local minutes and seconds are the same youcan only set local hours 4 17 CHRONOMETER MODES TIME FUNCTIONS UTC UNIVERSAL TIME COORDINATED Simply move the selector to the UTC position The display will show universal time in hours minutes and seconds A distinct graphic pattern is also displayed to indicate that the time mode is active LOC LOCAL TIME 22 of 27 Feb 25 2005 Symphony SA160 Move the selector to the LOC position The display will show LOCal time in hours minutes and seconds A distinct graphic pattern is also displayed to indicate that one of the two time modesis active FLT FLIGHT TIMER Move the selector to the FLI position The display will show the total time in hours minutes and seconds since the system was last powered up This is useful for your log book entries and in flight time keeping Be sure to note the FLT time before shutting off the master as it is cleared at next power up COUNT UP STOP WATCH FUNCTION STEP 1 Move the selector switch to the STOP position The display will freeze STEP 2 When you want to begin timing simply move the selector to the RUN position and the display will begin counting up An additional feature
207. ths annual and in addition to this inspection aircraft operated commercially for hire must have a complete inspection every 100 hours of operation in order to keep the Certificate of Airworthiness in effect Applicable inspection items for 100 hrs or annual inspection are specified by the airworthiness authority of the respective SA 160 owners The SA 160 Inspection Time Intervals Chart should be used as specific augmentation but it is not intended to be utilized as the primary checklist for inspection of the aircraft The required inspections should be accomplished by a properly trained and qualified mechanic of an authorized SAI Service Station SAI will not accept responsibility for the continued airworthiness of an aircraft not maintained to these standards and or not brought into compliance with applicable Service Bulletins issued by SAI instructions issued by the engine propeller or accessory manufacturers or Airworthiness Directives issued by the national Airworthiness Authority 8 5 PREVENTIVE MAINTENANCE A certified pilot who owns or operates an aircraft not used as an air carrier may be authorized by its local airworthiness authority to perform limited preventive maintenance Please refer to the specific local airworthiness authority to determine specific maintenance procedures which are allowed Feb 25 2005 8 4 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 All other maintenance operat
208. tim System detener re tar re Aaa ROA 7 60 7 43 Stall Warning System nee ica 7 62 TAD AVIONICS sieve exis 7 62 a Radio and Intercom erre 7 62 b Transponder teet tette 7 63 7 47 Emergency Locator Transmitter ELT nennen 7 66 Fig 7 1 Aileron Control System sss 7 8 7 2 Elevator Control System esaet tinent 7 9 7 3 Rudder Control System sess 7 10 7 4 Instrument Panel eem iio 7 12 Zb VM 1000 SchematiC canas 7 20 7 6 VM 1000 Indicator ttt eines 7 22 7 2 Feb 25 2005 Symphony SA 160 TABLE OF CONTENTS CONTINUED Fig 7 7 BC TOO Display neret A 7 24 78 LeaningMode nte mentre ttes 7 26 7 9 Fuel System Schematic cepe edens 7 32 7 10 Fuel Shut Off Valve i e ere a aaa ledit 7 33 PAL Fuel Level indicati i an ado 7 34 7 12 Drain Valves edo Wo ene te aer tenens 7 36 7 13 Drain Valves on base wing fuel thanks 7 37 7 14 1 Electrical Power Distribution sss 7 41 7 14 2 Electrical Power Distribution sese 7 42 7 15 Circuit Breaker Panel iwo AO EE 7 44 7 16 Static and Pitot Pressure System Schematic 7 49 7 17 Va cum System teet A 7 51 7 18 INTERCOM Control Panel sssrini 7 54 7 18 NAV COM Receiver Transmitter eee 7 54 7 19 Transponder Front View eese 7 55 7 20 ELT Remote Switch Annunciator
209. to activate the Lean EGT Mode Notice that the graphic display changes its appearance The graph is normalized to the bottom to give you a baseline reference while leaning Each bar represents ten degrees in this mode STEP 2 LEAN the engine mixture smoothly to start the bars climbing about one bar per 2 seconds The computer monitors all EGT values and detects the first EGT to lean out When this happens the bar graph for that EGT will begin flashing and if optionally equipped an audio visual alert occurs This is your signal to stop leaning NOTE Ifit looks asif the graphs will fill up Feb 25 2005 13 of 27 Symphony IRCRAFT SA160 before you achieve leanest EGT you can simply reinitialize by pressing BUTTON 1 twice which re arms the Lean EGT mode and normalizes the graphs to the bottom again Do notlean further if engine roughness occurs STEP 3 ENRICH after the lean EGT graph stops flashing noting that the lean EGT graph the graph that now has a single bar marking where the peak was found goes up This signifies that the mixture is returning to the peak value again Set your final mixture via the bar graph or by the digital readout now showing the leanest EGT according to your particular engines operating handbook Some engines require a mixture 50 75 degrees rich of peak at high power settings while others allow running at peak or even leaner Consult your engine manual TIP Initially set a rich fuel
210. travel to and from the ground station The groundspeed feature incorporated in the unit measures the rate of change in DME slant range distance with time The DME system can be turned ON if the BAT switch and the AVIONIC II switch are in the ON position a Key and Knob Functions The 3 position function switch determines both the information displayed and the channeling source Three modes can be selected 1 FREQ Mode The unit is channeled internally with its own frequency selection knobs The unit will display distance and the selected frequency Feb 25 2005 5 of 6 SECTION 9 gt ymphony SUPPLEMENT 5 SA 160 2 GS T Mode The unit will hold the internally selected frequency and will display distance groundspeed and time to station 3 RMT Mode The DME will be channeled by selecting NAV frequency on the NAV receiver When the unit locks on a ground station it will display distance groundspeed and time to station Prior to lock on dashes will be displayed With the frequency selection knobs O the desired DME ground station frequency is selected 1 The outer larger knob O changes the larger digits 1 MHz 10 MHz 2 The smaller knob O changes the 0 1 MHz digit 0 0 0 1 0 2 etc When pulled out it adds 0 05 MHz to the frequency and tunes in 0 1 MHz steps 0 05 0 15 0 25 etc Pushing this knob in subtracts 0 05 MHz from displayed frequency r Ground Speed Time to S
211. tude the first step is to prepare for an emergency landing Promptly establish a glide attitude and secure the speed for best gliding angle 74 KIAS Trim the aircraft and look fora field suitable for landing If altitude permits move the mixture control to RICH and check the auxiliary fuel pump and if required switch to ON It supports the fuel supply to the engine if the engine driven fuel pump has failed Switch the carburetor heat to ON Check to ensure the ignition switch isin BOTH position WARNING At airspeeds below 75 KIAS the propeller can stop no autorotation In this event increase the airspeed to autorotation or turn ignition 3 12 Feb 25 2005 Symphony SA 160 Symphony SECTION 3 SA 160 EMERGENCY PROCEDURES switch to START to start the engine Check the fuel valve is in ON position and the fuel quantity in the wing tanks is sufficient By examining the engine parameters it is usually possible to determine the cause of the power loss and rectify the situation As soon as the engine power is restored and if the failure cause was not carburetor icing move the carburetor heat to the OFF position If power is not regained proceed with the Landing Without Engine Landing Without Engine Power gt Checklist 3 5 d The gliding air speed of 74 KIAS flaps up and 65 KIAS flaps 20 delivers minimum loss of altitude in a given time Over a distance of 1 6 NM the loss of altitude is 1000 ft
212. uel supply to the engine during a possible short term interruption of the fuel flow from the wing fuel tanks This may occur during descend with high nose down attitude when the wing tank have little fuel remaining since the fuelis draw off from the rear part of the wing fuel tanks However the size of the feeder tank guarantees a secure fuel supply to the engine during longer descents Feb 25 2005 7 31 SECTION 7 Symphon Y DESCR amp OPERATION SA 160 FUEL SYSTEM SCHEMATIC A Fuel Venting M ni ZAP r Wing Fuel Tanks E Fuel ver Line bw VM 1000 INTERFACE O Air Bleeder 2 Drain Valves 3 Check Valves A gt de Fuel Shut Off Valve Fuel Pump Fuel Pump GI UI v Aux Fuel Pump Gascolator JJ o E d Carburetor Fuel Pump Drain Valve Figure 7 9 Fuel System Schematic 7 32 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION WARNING GJ With less than 10 liters 2 5 Gallons per each wing tank red arc a indicator power on descents with flaps extended must be limited t maximum 10 minutes duration After 10 minutes of descend in this regime a three minute level flight attitude with flaps retracted is to be accomplished From the
213. uld complicate the starting process because of their power consumption Check the fuel valve is in ON position for fuel supply Feb 25 2005 4 21 SECTION 4 gt ymphony NORMAL PROCEDURES SA 160 c Starting Cold Engine 4 5 c Set the brakes and turn on the alternator and the strobe light At night turn on the instrument and map lights They should be switched on to check the engine parameters on the VM 1000 display during start Check the carburetor heat is OFF It is recommended that when starting a cold engine prime it by pumping throttle one to three strokes In this way extra fuel becomes injected directly into the cylinder fuel air induction system Then open the throttle lever approximately 6 mm 1 4 in Set the MIXTURE lever to the FULL RICH position For aircraft equipped with a primer system it is recommended that when starting a cold engine prime it max 3 strokes and secure the primer button WARNING Overpriming complicates the engine starting process it may resultin a discharge of fuel or even an engine fire A unlocked primer button can affect negatively to engine Operation After ascertaining that the propeller area is clear of people 6 meters engage the starter by rotating the ignition switch clockwise As soon as the engine fires release ignition switch and move the throttle to attain 1000 1200 RPM If the engine does not fire within 5 10 seconds disengage the starter and repeat starti
214. ure that the feet of the non flying individual are clear of the brakes and rudder pedals 7 15 WING FLAP SYSTEM The SA 160 employs electrically actuated Fowler flaps which can be extended from 0 40 without increments The left flap is directly connected to an electrical flap actuator through a bellcrank and a pushrod The right flap is driven through control cables abellcrank and a pushrod The flap position indicator is located on the instrument panel right to the row of control switches 7 14 Feb 25 2005 Symphony SECTION 7 SA 160 DESCR amp OPERATION From the retracted position 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 reach the 40 position To retract the flaps the flaps switch must be placed in the upper position from the neutral position The switch will remain in the upper position until reset to neutral After the complete or partial flaps retraction the flaps switch is to be set into neutral position A micro switch will stop the full flaps retraction at the 0 setting A yellow annunciator light Flaps in Motion indicates that the flaps are in transition The light is located beside the EC 100 Display above the flight instruments Figure 7 2 The light will illuminate whenever the flap actuator is in operation The purpose of this light is to inf
215. use the following procedure 1 Park the aircraft in a hangar or in the shade avoid places with a lot of dust caused by wind or vehicles 2 To prevent scratches wash the windows carefully with plenty of a mild soap and water solution using the palm of the hand to feel and dislodge dirt and mud Asoft cloth chamois leather or sponge should be used 3 Rinse thoroughly and then dry witha clean chamois 4 Wax the surface with a good commercial wax in accordance with manufacturer s instructions Feb 25 2005 8 12 SECTION 8 gt ymphony GROUND HANDLING SERVICING amp MAINTENANCE SA 160 5 Remove oil and grease with a cloth moistened with isopropy alcohol CAUTION Never use gasoline benzene alcohol acetone carbon tetrachloride lacquer thinner or glass cleaner These materials will soften the plastic and may cause it to crack Do not use cleaners with such chemical supplements whose effect is unknown on the windows surface b Exterior Surfaces For cleaning the exterior surfaces use the following procedure 1 Park the aircraft in a hangar or in the shade avoid places with a lot of dust caused by wind or vehicles 2 Close doors if open close access inspection plates CAUTION Keep water away from pitot and static ports electrical and avionics equipment Do notuse harsh abrasives alkaline soaps or detergents 3 Flushaway loose dirt with water 4 Using a soft cleaning cloth or a spon
216. utput level is adjustable by your avionics installing agency The GMA 340 s marker beacon receiver controls are located on the left side of the front panel The SENS button selects either high or low sensitivity as indicated by the HI or LO LED being lit Low sensitivity is used on ILS approaches while high sensitivity allows operation over airway markers or to get an earlier indication of nearing the outer marker during an approach 10 of 11 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 3 The marker audio is selected initially by pressing the MKR mute button lf no marker beacon signal is received then pressing again will deselect the marker audio This operation is similar to selecting any other audio source on the GMA 340 However ifthe 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 that the source is still selected The GMA 340 s SmartMute function then monitors the marker signal and automatically unmutes the audio when the current marker signal is no longer being received In all cases the marker beacon lamps operate independently of any audio selection and cannot be turned off The GMA 340 can drive external marker lamps if required Feb 25 2005 11 of 11 Symphony SA160 Symphony uu Airplane Flight Manual Supplement Model SA 160 SUPPLEMENT 4 GARMIN GTX 327 MODE A C TRANSPONDER
217. when fuel is being burned The graphic display is shut off as it has no relationship to this parameter BRN This mode displays the gallons of fuel burned in flight since system power up It is digitally displayed in 0 1 gallon increments The graphic display is shut off as it has no relationship to this parameter ADD This mode allows you to add fuel to the fuel computers electronic tank after fuel has physically been added to the aircraft tanks See section on ADDING FUEL TO THE COMPUTER Feb 25 2005 11 of 27 Symphony IRCRAFT SA160 4 9 CYLINDER ANALYZER SYSTEM OPERATION The engine analyzer system displays all cylinder information both graphically and digitally Full color reference marks are provided for cylinder head green yellow and redline temperatures DIAMOND GRAPH DISPLAY MODES NORMAL MODE The system powers up in this mode and is ready for flight 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 observed A defective CHT or EGT probe will leave the respective graph blank A flashing CHT graph indicates a cylinder is too hot or is being shock cooled 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 leaning The display can be returned to t
218. x 1 minutes allowing you to access otherinformation To quickly return to the beginning display press both the and buttons until you see the beginning display 4 20 FUEL LEVEL SYSTEM OPERATION Feb 25 2005 25 of 27 SECTION 9 gt ymphony SUPPLEMENT 6 SA160 The fuel level system operates automatically once the FUEL LEVEL SYSTEM CALIBRATION has been performed The indicator displays a left center and right digital read out of the units of fuel remaining of up to 99 units per tank Additionally the left and right displays are also presented graphically to show percentage of fuel remaining for quick reference WARNING GJ AIRCRAFT ATTITUDE AND OTHER FACTORS CAN AFFECT THE ACCURACY OF THE FUEL LEVEL READINGS AFTER INSTALLATION AND PERIODICALLY THEREAFTER VERIFY THAT THE SYSTEMS ACCURACY IS ACCEPTABLE FOR YOUR INTENDED USE If a probe is not installed or not functioning that display is blanked An unsteady display value should be suspect and possibly disregarded as faulty operation Fuel Level Alert A low fuel level alarm has been incorporated into the system which signals you when a minimum fuel level has been reached in a given tank by displaying Lo in the corresponding display area This value is picked at our factory but may be specified upon written request at the time fuel calibration information is submitted to us SECTION 6 PERFORMANCE Nochange 26
219. x oil level 7 6 liter 8qt 6 Adjust the seats to the maximum forward position 7 Retract the flaps completely 8 Putall control surfaces in the neutral position 7 CAUTION Whenever the fuel system is completely drained and fuel is replenished it will be necessary to run the engine for a minimum of three 3 minutes at 1000 RPM in order to ensure that no air remains in the fuel supply lines b Leveling 1 Place properly calibrated scales with the corresponding load carrying capacity under each wheel 2 Using the aircraft marking for longitudinal leveling shown in Figure 6 2 level the aircraft by changing the air pressure in the nose wheel tire to center the bubble on a spirit level Feb 25 2005 6 3 SECTION 6 gt ymphony IRCRAFT WEIGHT AND BALANCE SA 160 c Weighing Aircraft Basic Empty Weight 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 form of Figure 6 1 The standard empty weight includes the required oil level 7 6 liters 8 qt and 12 liters 3 1 US Gal unusable fuel 6 4 Feb 25 2005 Symphony SECTION 6 SA 160 WEIGHT AND BALANCE AIRCRAFT WEIGHING FORM MODEL SERIAL NUMBER REGISTRATION DATE NUMBER LEVELING DIAGRAM REFERENCE DATUM AIRCRAFT AS WEIGHED CG CZ
220. y of the engine sump is 7 6 Liters 8 U S quarts The oil passes through an oil suction strainer screen into the engine driven oil pump and then to the engine parts to be lubricated A bypass valve on the oil pump allows cold oil passage and directs hot oil from the engine to the oil cooler After the cooling oil return it passes the full flow oil filter again and into the engine The oil pressure is held constant by an oil pressure relief valve which allows excessive oil to return to the sump After lubrication the oil flows back into the sump again by gravity The oil filler cap oil dipstick for oil level check is located at the right rear of the engine It is accessible through a small access door on the top right side of the engine cowling CAUTION GJ The engine should not be operated on less than 5 Liters 5 2 U S quarts of oil g Cooling System The engine cooling air enters through two intake openings located in front of the engine cowling on both sides of the propeller The air is then directed by air baffles around the cylinders and other relevant areas of the engine The air is discharged through an opening at the bottom rear edge of the cowling h Exhaust System The exhaust system is constructed of stainless steel and incorporates a main exhaust with a heater shroud and a secondary exhaust The heater shroud supplies heated air for the cabin and the defroster system Feb 25 2005 7 29 SECTIO
221. yed on the second CDI SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in the paperwork delivered with the aircraft 10 of 15 Feb 25 2005 Symphon Y SECTION 9 SA160 SUPPLEMENT 2 SECTION 7 DESCRIPTION AND OPERATION 7 1 GENERAL The information contained in here supersedes the information on the Bendix King KX 125 VHF NAV COM receiver transmitter provided in the Description amp Operation Section of the basic Pilot s Operating Handbook and TC Approved Airplane Flight Manual For a complete description of the GNC 420 system refer to the GARMIN GNC 420 Pilot s Guide P N 190 00140 20 Rev A dated July 1999 or later appropriate revision 7 2 SYSTEM DESCRIPTION The GNC 420 system consists primarily of the GNC 420 unit a GPS antenna and a VHF COMM antenna The GNC 420 unit contains the GPS Receiver and the VHF Communications Transceiver The unit is mounted in the center of instrument panel inthe avionics column Feb 25 2005 11 of 15 SECTION 9 gt ymphony SUPPLEMENT 2 SA160 GNC 420 VJ RNG A FPL Figure 7 1 Front View of the GNC 420 Unit a Key and Knob Functions 1 Unit Keys and Knobs Excluding bottom row The COM power volume knob c controls unit power and communications radio volume Press momentarily to enable disable automativ squelch control The

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