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SN3500 Installation Manual

1. RIGHT SIDE VIEW 8 7 5 3 2 1 NOTES UNLESS OTHERWISE SPECIFIED INITIAL RELEASE COMPUTER GENERATED DRAWING DO NOT REVISE MANUALLY BACK VIEW ITEM PART OR NO IDENTIFYING NO NOMENCLATURE OR DESCRIPTION MATERIAL SPECIFICATION QTY REQD PARTS LIST UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE FRACTIONS DECIMALS ANGLES CAD GENERATED DRAWING DO NOT MANUALLY UPDATE APPROVALS DATE SANDEL DRAWN EN X X XX 0l 5 MCLANE 03 09 05 nq LAYOUT SN3500 MATERIAL AR RESP ENG SN3500 USED SIZE CATEGORY DWG NO REV B 82005 FRONT VIEW APPLICATION DO NOT SCALE DRAWING APPROVAL 8 7 5 T 3 2 o 2 4 2 2 REVISIONS NOTES UNLESS OTHERWISE SPECIFIED ee 0 1 LOCATE CLAMP TRAY WITH SUFFICIENT CLEARANCE ABOVE amp BELOW A POSITION THE SANDEL FLUSH MOUNTING SHIM 61062 BETWEEN THE BACK SIDE OF THE INSTRUMENT PANEL 0 AND THE CLAMP TRAY NOTE THE LOCATION OF THE CHAMFER ON THE CORNER OF THE SHIM eee STARTING AT THE BOTTOM SCREWS ATTACH THE CLAMP TRAY TO THE INSTRUMENT PANEL WITH 1 EA 8 52 X 2 AND 6 52 X 75 BOTTOM AND 1 EAS 8 32 X 2 AND 6 32 X
2. LABEL DESCRIPTION ADF 162 ADF Bearing Gyro AHRS 155 Maintenance Words Sandel SG102 Only 270 AHRS Status Information when available 320 Magnetic Heading 324 Pitch 325 Roll 332 Lateral Acceleration 350 Maintenance Words Sandel SG102 Only 351 Maintenance Words Sandel SG102 Only 352 Maintenance Words Sandel SG102 Only 353 Maintenance Words Sandel SG102 Only 354 Maintenance Words Sandel SG102 Only TCAS 013 Control Word for TCAS Mode S 015 Altitude Select Limits for TCAS Mode S 016 Control Word for TCAS Mode S 130 Intruder Range 82005 IM K 362 131 Intruder Altitude 132 Intruder Bearing 203 Altitude 1013 25 mB 204 Baro Corrected Altitude 320 Magnetic Heading 371 General Aviation Equipment Identifier 377 Equipment Identification 357 Request To Send RTS End Transmission ETX NAV 034 VOR ILS Frequency 173 Localizer Deviation 174 Glideslope Deviation 222 VOR Omnibearing 371 General Aviation Equipment Identifier TACAN 201 TACAN Distance 202 TACAN Distance 222 TACAN Bearing 246 TACAN Station ID Characters 1 2 247 TACAN Station ID Characters 3 4 TACAN Range Rate Sandel SN3500 Installation Manual Page 2 15 LABEL DESCRIPTION DME 035 DME Frequency 202 DME Distance GPS FMS 076 GNSSS
3. A B C D E DATE COMMENTS Tar wa veo mon CHANGES SS COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY STEC AERONETICS 8100 SANDEL SN3500 GYRO AND 8140 FLUXGATE 2200 1 8 w or larger SEE NOTES 1 2 amp 3 6446 8140 Fluxgate FLUXGATE X maad Fluxgate FLUXGATE Fluxgate FLUXGATE 2 U U Fluxgate Z Exc C FLUXGATE EXCITATION Exc H Exc 6444 8100 Exc C GYRO PHASE 1 400 Hz EXCITATION 2200 1 4 w or larger DGX RAS DG X DG Y DG Y s aqa EGRE E C U Bos PER MFG S SLAVING INSTALL MANUAL SLAVING AVIONICS BUS POWER GROUND 26VAC 400HZ EXCITATION FOR EXTERNAL USE 1 SYNCHRO LOAD MAXIMUM NOTES 1 THE STEC AERONETICS GYRO DOES NOT ALLOW THE USE OF AN EXTERNAL 400HZ INVERTER FOR ITS XYZ OUTPUTS IF AN EXTERNAL INVERTER IS NEEDED TO DRIVE OTHER SYSTEMS WHICH ARE CONNECTED TO THE SN3500 THIS GYRO IS COMPATIBLE 2 THE 2200 OHM RESISTORS ARE RECOMMENDED NOT REQUIRED TO REDUCE RINGING FROM THE INTERNAL INVERTER THE SN3500 APPLIES NO LOAD TO THE GYRO 3 EARLY MODELS OF AERONETICS GYROS OPERATE AT 600HZ AND ARE NOT COMPATIBLE WITH THIS SYSTEM CONTACT STEC FOR S N INFORMATION ANDEL Vista Ca TEC AERONETICS GYRO Size Document Number Rev 82005 10 reate Tuesday September 19 2000 Mod Sunday December 09 2007 Sheet 12 E DATE COMMENTS PA A R 780 MINOR DOC CH
4. and software Configuration Field Options Comment Rmt Switch Annun NO Set to yes to allow SN3500 to control YES GPS switch inputs LEG OBS switching APPR ARM etc through Pilots Menu Available options will depend on the model of GPS selected on the GPS maintenance page Discr Out None Selects which pin connector pin is P3 2 assigned to TACAN Relay Out Signal P3 10 Install Position PLT ONLY Set to adjust color of on side cross side PLT DUAL NAV information COP DUAL Hdg Bug Color Orange Heading bug color selection White Aircraft Ident 7 characters Enter aircraft identification for reference 82005 IM K Sandel SN3500 Installation Manual Page 7 3 7 1 3 Page 3 COMPASS SYSTEM SANDEL 3 COMPASS SYS p VALUE R 3 E VOLT V PINS FUNC C R BRG MEM Appendix A Post Installation Procedures The Compass System page configures the gyro and fluxgate if applicable to the SN3500 Configuration Field Options Comment HEADING NONE Selects the gyro input to the SN3500 429 429H XYZ XYZ MID CONT KG102 VALID NONE Not shown if 429 or 429H is selected for HIGH heading LOW FLXGATE NONE Selects model of fluxgate input when KMT112 slaving is performed internally COLLINS HONEYWELL STEC 6446 QUAD 0 0 Set automatically when fluxgate is 90 0 selected 180 0 270 0 PEAK 0 7 Set automatically when fluxgate is selected 82005 IM K Sa
5. T F w X a lt er OWENS SM Configuration Field Options Comment SOURCE NONE Set to 232 to enable WX 500 interface 232 MODE IS n a Displays current mode of the WX 500 MODE RQ WEATHER Selects mode of WX 500 Select STRIKE TEST WEATHER for normal operation DEMO NOISE MONITOR SELF TEST ANT IS n a Displays current antenna configuration ANT RQ TOP Software selection of antenna location BOTTOM Normally not used as the antenna UNKNOWN location is set by jumpers on the WX 500 INFO RQ FAULT LIST Requests information from WX 500 CONFIGURATION Information will be shown at the bottom ENVIRONMENT of the display S W VERSION 82005 IM K Sandel SN3500 Installation Manual Page 7 22 7 1 12 SANDEL Page 12 Traffic 12 TFC amp WXDL VALUE P R PINS E V FUNC N A v G F w X CER j BRG MEM Appendix A Post Installation Procedures Configuration Field Options Comment DATA LINK WSI w TX SN3500 is sole display Software version SN3500 is wired as receive only 3 00 and above WSI no TX another display is connected to the WSI receiver DLINK KEY Blank by default Enter the purchased 11 character Software version key code to enable data link weather 3 00 and above Use the BRG and MEM keys to select the character and the MAP and TFC keys to move the cursor TCAS KEY Blank by default Enter the purchased 11 chara
6. aes aded eere a eee dre eee 11 6 11 332 GPSInterface and Control etd oec o ee ear dds 11 7 11 1 13 Marker Beacon Interfaces 5 2 ioc io ee dI eel ee e HO Lade pee 11 8 11 1 14 Flight Control System Interface l U 11 9 11 1 15 Stormscope Interface ero her ie tee eden n Po ete dpt 11 9 111 16 UIralfio eno Eee tto tote e oen te Da cm aout 11 9 11 117 NVIS Gorttlolus su oe nee ere eta e te eA e errands 11 10 11 1 18 Reversionary Display Control u tetti ntn 11 10 11 1 19 Additional terns etna te tete 11 10 11 2 EMI RFI Test 2 u u uu uuu 11 10 11 22 Testing uu uqa ioi ea reete erede hn ere eie db tec a aide 11 10 11 22 General Testing oii cti n iride tee tc eC de ada eae 11 11 14 2 3 Additional Testing ote te taz rene dani a ie dd 11 12 11 3 Operational Flight Test Procedures Reporrt essent nennen nennen 11 13 11 4 eerie eee ente utendi 11 15 11 5 Test Procedures ei i veda 11 15 11 5 1 Pre Departure Operations I essent L 11 15 11 5 2 Enroute Operations uuu uU u au a essen ense 11 16 11 5 8 GPS Approach OpAeTatio S L u u u aan aa
7. INSTALLATION SPECIFIC RELAY POLES WHICH MAY ALSO BE EM NEEDED LRN WPT IN 6 FOR 3V COMPOSITE NAV SOURCES INSERT A 470K SERIES RESISTOR WPT ANNUN RS232 TX j LOCATED AT THE SN3500 CONNECTOR NOT REQUIRED FOR 5V SOURCE HN j RELAY SENSE NOTE 7 P3 4 GPS1 SENSE 7 ONLY USED WHEN SN3500 IS IN MASTER MODE SELECT GPS1 FOR SENSE ON OBS RELAY CDI MAINTENANCE PAGE APPR ARMIN 8 10 APPRARM OUT HEP ACFT PWR INSLAVEMODETHE RELAY DRIVE IS PART OF THE EXTERNAL aT 1N4004 SANDEL Vista Ca SWITCH ANNUNCIATOR MASTER MODE 4 Category y mM a GPS1 RELAY SN3500 INSTALLATION DRAWING ee ee CALCE e itle GPS ENABLED FROM SLAVE MODE gt NAV 1 RS 232 GPS NT RELAY SWITCH ANNUNCIATOR UNIT O GPS SELECTED ize Document Number Rev GPS SWITCHING RELAY CONNECTIONS SEE NOTE 4 B CONNECT P3 4 OR P3 7 BUT NOT BOTH 82005 1 0 reate Tuesday April 28 1998 Sheet 21 E DATE COMMENTS A INITIAL RELEASE FROM VRE NAY RECEIVER TOAUTOPICOT At A R780MINOR DOC CHANGES GPS LORAN RECEIVER 2 C PTPLANDPITREVERSED Pm 29443453440 44445453415 _NOTE7 SN3500 KLN 90B SHOWN FOR Ha uum lark ADDED KLN90B SDI 1 2 CONNECTION ADDED REFERENCE ae lt l
8. 9494 ONLY STATOR D 21 Rd S TO TO NOTES FROM FROM ACTIVE OUTPUT CHECK APPROPRIATE NAV RECEIVER SCHEMATICS CONNECT SIN OUT and COS OUT TO THE ACTIVE RETURN PINS C USUALLY D F CONNECT OBS VREF TO EITHER STATOR RETURN PIN E REF OR GROUND USUALLY E G THE LOAD RESISTOR SIMULATES SYNCHRO S RECEIVER SIGNAL GND H N Q 2 THESE CONNECTIONS FOR 165 OR KNX80 81 PREVENT THE RECEIVER DOM 23 OBS RESOLVER H IN FROM FLAGGING THE NAV SIGNAL WHEN THE RESOLVER IS BEING USED BY OBS OUT E THE GPS CONSULT THE APPROPRIATE KING DOCUMENTATION FOR NOTE 1 G Q FURTHER INFORMATION N G o 37 OBS RESOLVER E VREF IN OBS RETURN F O 3 SEE ARINC 429 INSTALLATION PAGE WHICH DOES NOT REQUIRE THE Q 4 RESOLVER SWITCHING RELAY WHERE APPLICABLE 8 OBS RESOLVER SIN OUT OBS SIN D O 4 THE PREFERRED INSTALLATION IS THE SN3500 P3 7 CONTROLLING AN 2 Q 4 EXTERNAL SWITCHING RELAY IF AN EXISTING SWITCH CONTROL BOX IS OBS COS 38 OBS RESOLVER COS OUT INSTALLED AND IT IS DESIRED TO LEAVE IT OPERATIONAL USE P3 4 TO SENSE GPS MODE AND SELECT SLAVE FOR THE MODE SETTING ON THE RS232 1 RX 3 OBS RELAY CDI MAINTENANCE PAGE GPS DISPLAYED 31 Q l RS232 1 GROUND 1 MASTER SN3500 CONTROLS THE NAV GPS SWITCHING PREFERRED 2 SLAVE EXTERNAL NAV GPS SWITCH CONTROLS THE SN3500 wo MSG ANNUN 29 LRN MSG IN 5 CHECK MANUFACTURERS DOCUMENTATION FOR ANY ADDITIONAL
9. FG EXCITATION SCHEMATICS BEFORE APPLYING POWER TYING PINS E G TOGETHER AS SHOWN ASSUMES THEM TO BE THE NAV RECEIVER VREF THESE ARE NORMALLY TIED TOGETHER INSIDE THE NAV RECEIVER AND GO TO SIGNAL GROUND OR AN INTERNAL DC REFERENCE VOLTAGE IF THESE DO NOT TIE INTERNALLY PLEASE CALL SANDEL FOR ASSISTANCE 4 WHEN CONVERTING KCS 55 SYSTEM INSTALLATIONS THE KA 51 SLAVING ACCESSORY IS NOT USED THE FLUXGATE EXCITATION SIGNAL CAN BE PICKED UP FROM THE EXISTING KA 51 CONNECTORS AS SHOWN 5 PRIOR TO INSTALLING THE SN3500 ENSURE THAT THIS WIRE IS COMING FROM THE FLIGHT CONTROL SYSTEM GROUND AND THAT NO VOLTAGE IS PRESENT ON THIS PIN WITH POWER APPLIED TO ALL AVIONICS IF VOLTAGE IS PRESENT CONNECT SN3500 P1 1 TO FCS GROUND AT THE ROLL COMPUTER WITH A NEW WIRE IF PRIMARY POWER IS APPLIED TO SN3500 P1 1 DAMAGE MAY OCCUR TO THE SN3500 RESULTING IN AN OPEN CIRCUIT AT P1 1 THIS CAN BE CHECKED WITH AN OHM METER FV EXT HI H FV EXT HI FV EXT LO 0 FV EXT LO FV X FV Y FV EXT HI FV EXT LO FV X 6 RESISTOR MAY BE REQUIRED SEE RESOLVER INTERCONNECT SHEET TO DETERMINE PROPER CONNECTION m o KA51 IOAM 51 gt SEE NOTE 4 SLAVE METER GROUND 5v 5V SLAVE 96113500 INSTALLATION DRAWING KCS 55 REMOVAL REF Bl Document Number 82005 10 reate Saturday May 02 1998 Mod Sunday December 09 2007 Sheet 19 CW j CW CCW t l l i l l l l l i l l l i l l l l l l
10. gt Q5 m m 8 on AN N bn 59 5 55 25 25 To 4 Sa 5 S g5 5 SS L 60 qx ROTOR DRIVE ROTOR RET STATOR REF P2 o m VIR351 CONNECTION TO OLDER RECEIVERS SUCH AS COLLINS 51R8 51RV 1 KING KNR660 AND SIMILAR RECEIVERS SEE NOTE 1 NAV RECEIVER 2200uF TO SN3500 2200uF 2200uF United LXF10VB222M or equivalent ARINC NAV RECEIVERS KNR634 AND COLLINS VIR 30A FOR VIR 30M SEE ABOVE SEE NOTE 2 VIR 30A KNR634 P2 P6342 OBS E COS OUT 37 OBS F SINOUT SN3500 2 22 25 400HZ DIFF RES COS IN 21 P2 22 52222 OBS TO FROM 22 lt 38 400HZ DIFF RES COS OUT EET DATE COMMENTS A INITIAL RELEASE At _A R780 MINOR DOC CHANGES L B MINOR CHANGES COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SN3500 RESOLVER DRIVE P2 23 5 RESOLVER H IN 38 OBS RESOLVER COS OUT 8 OBS RESOLVER SIN OUT NOTES 1 THE SN3500 REQUIRES DC FLAG SIGNALS SOME VERY OLD RECEIVER DESIGNS OUTPUT UNSMOOTHED DC DUE TO A LACK OF FILTERING CAPACITORS THE SN3500 WILL SHOW UNSTABLE FLAG OPERATION UNLESS SMOOTHING CAPACITORS ARE ADDED AS SHOWN THE CAPACITORS CAN BE MOUNTED ON A TERMINAL BLOCK NEAR THE RECEIVERS CONSULT THE RECEIVER SERVICE MANUAL SCHEMATICS AS REQUIRED 2 FOR ARINC NAV RECEIVER USING 400HZ DIFFERENTIAL RESOLVER a THE NAV RCVR AND SN3500 MUST BE ON THE SAME INVERTER b ON
11. Added optional superflag connection for reference and note 5 Modified note 4 for clarity COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SANDEL SN3500 AUTOPILOT HDG DATUM HDG DATUM HI CRS DATUM CRS DATUM HI SIGNAL GROUND CRS HDG DATUM LO Ground FCS LAT DEV FCS LAT DEV RIGHT p gt FCS LAT FLAG FCS LAT FLAG FCS LAT FLAG FCS VERT DEV UP MES pu E 5 FCS VERT FLAG A FCS_VERT_FLAG FCS_VERT_FLAG ILS ENERGIZE IN NAV GPS RECEIVERS FCS VERT DEV FCS ILS ENERG OUT SIGNAL GROUND FCS LATERAL SUPERFLAG EO le ee ee FCS VERTICAL SUPERFLAG ALTERNATIVE FLAG SIGNAL INVERTER EXC AUTOPILOT EXITATION 400 Hz to 5 KHz SEE NOTE 4 5 INVERTER OUT SIGNAL GROUND NOTES 1 IN THIS CONFIGURATION THE SN3500 ACTS AS THE AUTOPILOT SWITCHING RELAY AND OUTPUTS TO THE 2 AUTOPILOT WHATEVER NAV SOURCE IS SELECTED 2 THIS IS A GENERIC ILLUSTRATION REFER TO THE SPECIFIC DETAIL DRAWINGS FOR YOUR INSTALLATION 3 THIS SIMPLIFIES INSTALLATIONS WITH A SINGLE ANALOG NAV AND DIGITAL GPS OR MULTIPLE DIGITAL GPS 4 INVERTER CONNECTION NOT REQUIRED WITH AUTOPILOTS USING DC CRS HDG DATUM IF AUTOPILOT EXITATION IS USED SELECT DC SIGNAL ON FCS MAINTENANCE PAGE 5 IF AC COURSE AND HEADING DATUMS ARE USED WITHOUT USING EXTERNAL EXCITATION ON P2 10 400 HZ AC MUST BE CONNECTED TO P1 16 AND TO AUTOPILOT EXCITATION IN SELECT AC SIGNAL ON FCS MAINTENANCE PAGE S ANDEL Vista Ca e FCS
12. LEFT selected from list below SCL V D Default settings reset when FCS is selected from list below MIN V Default settings reset when FCS is selected from list below 82005 IM K Sandel SN3500 Installation Manual Page 7 18 Appendix A Post Installation Procedures MAX V Default settings reset when FCS is selected from list below REF V Default settings reset when FCS is selected from list below FCS Select from list Select the appropriate emulation from the list Press the SET soft key CLR button to program HDG V D and CRS V D increase or decrease the gain of the course or heading error relative to the lubber line and normally match the volts degree input of the associated autopilot computer These values default when the FCS selection is initially set but can be adjusted in flight if necessary in VFR conditions as follows a Engage the autopilot in HDG mode After the aircraft is established on the desired heading move the heading bug knob a large amount and ensure that the aircraft turns to the heading bug and rolls out normally without instability overshooting or undershooting to the desired heading To correct for overshooting or instability reduce the HDG V D setting To correct for undershooting increase the HDG V D setting b Engage the autopilot in NAV mode and turn off the NAV receiver to provide a zero course error Repeat the tests and adjustments above using the course po
13. SN3500 CD33 TO AMP PARALLEL ROLL EXC DATUM EXCITATION WITH EXISTING ROLL EXC WIRES 10K 10K CD33 TO DG Ti HDG DATUM ROLL COM 10K 10K CRS DATUM 27mH JW Miller PN 9250 276 or Equiv CENTURY 1C 388 C 1C388 MC RADIO COUPLERS CD33 TO DG P2 SN3500 ROLL EXC 10 DATUM EXCITATION ROLL EXC HDG SIG T ROLL COM 10K 10K 40 ICRS DATUM ABOVE COUPLERS DO NOT SUPPORT COURSE DATUM CENTURY 1C 388 2 RADIO COUPLER SN3500 CD33 TO DG P2 ROLL EXC DATUM EXCITATION ROLL EXC HDG DATUM CRS DATUM CENTURY 1C 388 3 RADIO COUPLER CD33 TO DG P2 SN3500 ROLL EXC 10 DATUM EXCITATION ROLL EXC HDG SIG Ti 26 HDG DATUM ROLL COM 10K 10K CRS SIG Ti 40 CRS DATUM ROLL COM 10K 10K E DATE COMMENTS INITIAL RELEASE _ A1 A R 780 MINOR DOC CHANGES COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY NOTES 1 SELECT NSD 360DC ON THE FCS MENU 2 ON FCS EMULATION MAINTENANCE PAGE ADJUST HDG GRADIENT AND CRS GRADIENT IF USED TO HIGHEST VALUE THAT DOES NOT OVER SHOOT THE LUBBER LINE DURING HDG MODE AND NAV MODE COURSE CHANGES RESPECTIVELY NORMALLY THESE VALUES WILL BE THE SAME 3 GROUND CONNECTIONS TO SN3500 SIGNAL GROUND 4 DO NOT GROUND ANY CENTURY II III SIGNALS EVEN DURING TROUBLESHOOTING THIS COULD DAMAGE THE AUTOPILOT SEE THE CE
14. Software Main 1 00 or later Main ARINC 429 IN 1 Low Sandel SN3500 Renhguration OUT Low GAMA 429 Grph w Int Note NOT ARINC 429 SDI LNAV2 SDI2 VORILOC GS Speed RX Low ARINC 429 Configuration Speo Tx Cow SDI VORIILS 2 8012 1 4 12 Special Considerations for UPS GXXX Configuration Notes GX Series Notes In Setup enable Extended MovMap Data Format SN3500 Unit Set LNAV selection to IIMorrow GX RS 232 ENH Vertical deviation if desired requires the ILS ENG input pin pulled low Testing The GX unit will not output RS 232 data in manual test mode Upon power on the GX will go through IFR Output Test Mode and the following test can be observed CDI amp Flags VDI amp Flags if enabled on Sandel Annunciators 1 4 13 Brightness Control Brightness control is internal through a pilot s menu No external brightness buss is used 1 4 14 Traffic The SN3500 supports Traffic input via single ARINC 429 High Speed Input on software version 2 01 and above Purchase of a key code to enable the Traffic display is required Some remote traffic processors may require remote switches see the Traffic interface drawings in this manual for these requirements When interfaced to a TCAS II remote processor the SN3500 can only be used as a secondary display as it will not display vertical guidance for the purpose of resolution advisories 1 4 15 Data Link Weather The SN3500 supports Flight Informati
15. l l l l l l i l l l i l l l i l l l l l l l l l l OBS SIN OUT i l l l l l l i l l l i l l l i l l l 1 l l l 1 l l l l l l l l l i l l l l l l l FROM VHF NAV RECEIVER TO AUTOPILOT 4 04 E n 22844483445 21454855224 fe c Ee s a aS hu S ps 1 1955424554 S 47749 uu SN3500 GPS LORAN RECEIVER m 2 gt gt _ 6_ KLN89 B SHOWN FOR 470K cD Composite 1 In ILS1 ENERGIZE REFERENCE FCS LOC ENGAGE VERT FLAG VERT FLAG GS Down Nav Flag VERT UP VERT DOWN LAT FLAG Nav Flag LAT FLAG Nav Left LAT RIGHT neve ONE TO TO FROM FROM KLN89 B SHOWN E SEE NOTE 3 TO VHF NAV S RECEIVER amp OBS OUT S OBS RESOLVER H IN SRS RUAN OBS RESOLVER E VREF IN OBS SIN OBS RESOLVER SIN OUT OBS RESOLVER COS OUT RS232 1 RX RS232 1 GROUND OBS COS GPS DISPLAYED MSG ANNUN ARM ANNUN APPR ANNUN WPT ANNUN RS232 TX LRN MSG IN LRN APPR IN LRN APPR ARM IN LRN WPT IN GPS1 SENSE APPR ARM OUT ees 25 APPR ARM IN PWR INSLAVEMODETHE K POWER GROUND RELAY DRIVE IS PART OF THE EXTERNAL GPS2 RELAY 1 d 1N4004 SWITCH ANNUNCIATOR d P UNIT GPS1 RELAY SLAVE MODE gt GPS SELECTED GPS ENABLED FROM
16. 50Hz I 17 PostScan X D7 Hz Y 245 1 WOHz ncuced Signal Suscepfibi Radio Requency Susceptibii Radio Reauency Emission ahtnna hduced Trarsien Susocptioiliy MEM amp P8 Fe Reemi 9 wa 3 82005 IM K Sandel SN3500 Installation Manual Page 8 2 Appendix C Sample FAA Form 337 9 Appendix C Sample FAA Form 337 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements 8 Description of Work Accomplished If more space is required attach additional sheets Identify with aircraft nationality and registration mark and date work completed A Installed the following equipment and components 1 Sandel Avionics Inc SN3500 Navigation Display or as appropriate Part Number SN3500 000 or as appropriate 2 Sandel Avionics LLC Clamp Fixture 3ATI Part Number 61062 B The Sandel Avionics SN3500 is interfaced to the following equipment 1 Garmin International GPS165 GPS Navigation Receiver Approved for En route Terminal and Non precision Approach or as appropriate 2 AlliedSignal Electronics and Avionics KX 165 Communications and Navigation Receiver or as appropria
17. 75 TOP PAN HEAD SCREWS COMPUTER CONTROLLED DRAWING D DO NOT REVISE MANUALLY 4 COMPLETE THE INSTALLATION PER INSTALLATION MANUAL SANDEL PART NUMBER 82005 IM CURRENT REVISION NOTE CHAMFER LOCATION SANDEL FLUSH MOUNTING SHIM SANDEL PART NUMBER 61044 CURRENT REVISION Eccc Z SANDEL 5 350 Jutta Q C GG 00000 0 E ES z 224 F B e UBT G MEM INSTRUMENT PANEL 6 32 X 75 2X FLUSH MOUNT INSTALLATION UNLESS OTHERWISE SPECIFIED A DIMENSIONS ARE IN INCHES VISTA LAYOUT 8 ue sees e e su3s00 INSTALLATION SN3500 m SUGGESTED PANEL CUT OUT FLUSH MOUNT Dl osl 82005 A nom 0 or sewe ome 102 B 7 6 5 4 3 2 1 NOTES UNLESS OTHERWISE SPECIFIED 1 LOCATE CLAMP TRAY WITH SUFFICIENT CLEARANCE ABOVE amp BELOW gt STARTING AT THE BOTTOM SCREWS ATTACH THE CLAMP TRAY TO THE INSTRUMENT PANEL WITH 1 8 32 X 2 AND 6 32 X 75 BOTTOM AND 1 EAS 8 32 X 2 AND 6 32 X 75 TOP PAN HEAD SCREWS 5 COMPLETE THE INSTALLATION PER INSTALLATION MANUAL SANDEL PART NUMBER 82002 IM CURRENT REVISION G XQ CO OC OO oO oo So SNES Oe 1 1111 SENEN S v INSTRUMENT PANEL STANDARD SATI INSTALLATION SN3500 6 32 X 75 2X 5 1 DATE COMMENTS INITIAL RELEASE E C A R 806 NEW PAGE NUMBER ADDED INVERTER 2 CORRECTED NOTE 2 JAN 12 2006 C1 A R 824 ADDED AD
18. A C power minus 2VDC 28V Aircraft A Ct power minus 4VDC P1 40 DME 2 Hold Discrete HOLD input signal for on screen annunciator P1 41 Inner Marker Beacon Input P1 27 Middle Marker Beacon Input P1 12 Outer Marker Beacon Input Marker beacon receiver inputs Normally connected to the external lamp drivers on the marker beacon receiver see the installation drawings Most marker beacon receivers use DC ground referenced outputs driven by transistor drivers All such receivers are compatible as shown on the installation drawings Some very old designs may use transformer outputs which are AC coupled These may not be compatible P1 42 ARINC1 429 A Output P1 28 ARINC1 429 B Output Low or high speed ARINC 429 output spare Future use 1 13 Ch1 RS 232 TX Output RS 232 serial data outputs TXD 2 is used to support WX 500 Stormscope 24 AWG shielded wire is required for each of these functions P1 43 WPT Annunciator input P1 29 MSG Annunciator input P1 14 ACT Approach Active Annunciator Input P1 44 ARM Approach Arm Annunciator Input Active low inputs for GPS LRN on screen annunciators P1 15 OBS LEG HLD AUTO or PAR TRK Annunciator Input For selected GPS 1 receiver with OBS LEG mode or HOLD AUTO this input when low senses and annunciates OBS or HOLD on the SN3500 display and changes the mode of the course pointer from auto slew to manual control Otherwise this is used as a PAR TRK input for other types
19. All configured items will be stored in non volatile memory NOTE When configuring ARINC 429 inputs select 429 for low speed and 429H for high speed Each maintenance page the options for each and a brief description of each option are detailed below 82005 IM K Sandel SN3500 Installation Manual Page 7 1 Appendix A Post Installation Procedures 7 1 1 Page 1 INDEX SANDEL 1 INDEX lt mav z z Axmz I uc F ly MODE CtR BRG MEM The Maintenance Index page is a multiple choice list that provides an index of all other maintenance pages and allows the operator to jump to a particular page First scroll the Cursor to point to the desired maintenance page listing using the UP Soft key or DOWN Soft key The SELECT Soft key is then pressed to jump to this page Once in the maintenance pages press the OPER Soft key to return to the Maintenance Index page The PREV or NEXT Soft keys may also be used to reach a particular maintenance page sequentially The MODE Soft key is used to toggle the SN3500 between READ and EDIT mode Note The SN3500 must be in EDIT mode to make configuration changes on the following maintenance pages 82005 IM K Sandel SN3500 Installation Manual Page 7 2 Appendix A Post Installation Procedures 7 1 2 Page 2 SYSTEM SANDEL 2 SYSTEM MD EECA The System page provides information that identifies the unit and the units hardware
20. Locate switch and placard nearest position available to SN3500 5 Assure adequate illuminatin of switch and placard for night operations under normal conditions 6 Use closest available airframe ground USING REMOTE GROUND SN3500 7 In the event of a broken wire fault the SN3500 will default to normal Reversionary Control Switch display non reversionary mode See note 8 See note 2 SG102 AHRS 8 Standard configuration is to use P3 6 for REV CNTRL If P3 6 is or equivalent device needed for Analog DME Valid see section 2 5 3 page 2 12 use T SG102 shown P3 13 NVIS REV ATT DME Analog Valid may not all be used simultaneously 429 A OUT 429 B OUT S ANDEL Vista Ca it m REVERSIONARY ATTITUDE DISPLAY OPTION Bl Document Number 82005 1 0 Create Mod Wednesday June 02 2010 Sheet 41
21. NOTES OBS RESOLVER E F VREF IN SWITCHING PREFERRED OBS RESOLVER SIN OUT EXTERNAL NAV GPS SWITCH CONTROLS THE SN3500 OBS SOP 4 CHECK MANUFACTURERS DOCUMENTATION FOR ANY ADDITIONAL INSTALLATION ARINC 429 TX A 429 1 RX A SPECIFIC RELAY POLES WHICH MAY ALSO BE NEEDED ARINC 429 TX B 429 1 RX B 5 KLN 90B PINOUTS SHOWN CERTAIN CONNECTIONS SUCH AS GPS_DISPLAYED JUMPERS REQUIRED IF NO ARINC 429 RX A AIRDATA COMPUTER 429 1 TX A SDI 1 2 AND OBS LEG ARE SPECIFIC TO KLN 90B ARINC 429 RX B INSTALLED 429 1 TX B 6 MSG AND WPT ANNUNCIATORS ARE COMMUNICATED ON THE ARINC 429 SERIAL ARINC 429 RX A 7 2 CHANNEL ARINC 429 RX B 7 FOR 3V COMPOSITE NAV SOURCES INSERT A 470K SERIES RESISTOR LOCATED AT THE SN3500 CONNECTOR NOT REQUIRED FOR 5V SOURCE APPR ACTIVE LRN APPR IN 8 ONLY USED WHEN SN3500 IS INMASTER MODE SELECT GPS1 FOR SENSE ON APPR ARM LRN APPR ARM IN OBS RELAY CDI MAINTENANCE PAGE 9 IF KLN90B IS USED FOR GPS1 LEAVE SDI 1 2 PIN 3 OF KLN90B OPEN IF KLN90B IS GPS DISPLAYED WIRED FOR GPS2 THEN CONNECT SDI 1 2 PIN 3 OF KLN90B TO GROUND GPS1 SENSE ARM SELECT APPR ARM OUT LEG OBS CTRL OBS CMND OUT IN SLAVE MODE THE RELAY DRIVE IS PART OF THE EXTERNAL ides 15 GPS2 RELAY SWITCH ANNUNCIATOR I 1 zd ES 7 GPS1 RELAY SANDEL Vista Ca 22200 613500 INSTALLATION DRAWING roses GPS ENABLED EROM GPS SWITCHING RELAY CONNECTIONS SEE NOTE 3 1 ARINC 429 GPS EXT
22. SANDEL 593500 HSI 3 COMPASS SYS p VALUE VOLT V PINS FUNC C 0 973 MEME BRG 78 Configuration Field Options Comment ATT Key Enter the Reversionary attitude key ATT Pin None Active L P3 6 Connector pin values do not appear in Active L P3 13 the ATT Pin selection field The appear above in the PINS field 82005 IM K Sandel SN3500 Installation Manual Page 7 6 Appendix A Post Installation Procedures 7 1 4 Page 4 ADF TACAN MKR SANDEL 4 ADF I TACAN MKR p VALUE R g VOLT V PINS zH z FUNC T F ic w X CER MEM The ADF page allows the selection for ADF1 ADF2 TACAN 1 TACAN 2 and Marker sources Configuration Field Options Comment ADF 1 NONE Selects type of ADF signal input f 429 bearing indication is off by 180 change 429H selection to opposite polarity XYZ XYZ S C DC S C DC VALID NONE Not shown if 429 or 429H is selected for LOW ADF source HIGH ADF2 NONE Selects type of ADF signal input If 429 bearing indication is off by 180 change 429H selection to opposite polarity XYZ XYZ S C DC S C DC VALID NONE Not shown if 429 or 429H is selected for LOW ADF source HIGH 82005 IM K Sandel SN3500 Installation Manual Page 7 7 Appendix A Post Installation Procedures TCN Key Blank by default Enter the purchased 11 character key code to enable T
23. range is 20Hz to 500Hz and calibration is done on the NAV maintenance page The resolver is electrically zeroed at zero degrees plus the calibration value in the NAV maintenance page For normal use this calibration value will be 60 degrees equaling 300 degrees electrical zero This is the factory 82005 IM K Sandel SN3500 Installation Manual Page 3 8 P2 24 P2 9 P2 39 P2 25 P2 10 P2 40 P2 26 P2 11 P2 41 P2 27 P2 12 82005 IM K Installation default A different calibration value setting is used for each possible NAV source selectable on the SN3500 24 AWG twisted shielded pair conductor is recommended for these functions Please see the warnings on the installation drawings concerning DC REF which must not be inadvertently grounded Flux Gate Excitation Input This connection is made to the 400 Hz AC flux gate excitation source voltage A 24 AWG shielded wire is recommended for this function Note the phase of this excitation voltage is not required to be the same as that supplied to the Primary AC Excitation input on P1 or P2 Flux Gate X Input Flux Gate Y Input Flux Gate Z Input Referenced to P2 24 Excitation input Connections to these pins are made directly from the heading system flux gate if internal slaving is selected on the compass maintenance page If a Bendix King KI 525 PNI or Rockwell Collins 331A 3 HSI is being removed the respective slaving accessory should be bypassed See the i
24. 11 17 11 54 TACAN Approach Operations L tetti a 11 17 11 5 5 IES Approach Operations ics I Rn G E eed EH ke EOD EHE Med ipe 11 17 1156 Additional Testing net teet ed be eite da ede RR Re tg 11 18 12 Appendix F List of Effective Drawings and Attachments 12 1 82005 IM K Sandel SN3500 Installation Manual Page v Revision History Revision Date 11 30 2010 Comments Updated for software version 4 03 AR1154 Section 1 1 1 Added TACAN ITAR Export Notice Removed NVIS notice Section 1 3 1 Added list of recommended crimp tools Section 2 2 2 Positronics P Ns added for connectors Section 2 6 1 Updated 429 Label Description table Section 2 6 2 Table formatting updated Section 7 1 14 Changes to maintenance page 14 added procedure for calibrating the minimum brightness when an external brightness control is used 05 27 10 Updated for software version 4 02 AR1110 Corrected TOC Section 3 3 2 Updated P2 3 35 pin description and added note for composite LOC DEV calibration procedure Section 7 1 2 New TACAN Relay out pin configuration Section 7 1 3 New Reversionary Attitude Enable pin configuration Section 7 1 5 Added composite LOC DEV calibration procedure Added reference to cal procedure and added GAIN selection to table Updated figure Section 7 1 6 Added reference to cal procedure and added GAIN selection to table Updated
25. 1999 Mod Wednesday July 30 2008 Sheet 28 SN3500 SN3500 SN3500 400 HZ REF IN X Y SHIELD GND SN3500 400 HZ REF IN X Y SHIELD GND ADF RECEIVER 1 2 INTERCONNECT ADF 1 400 HZ REF HI 400 HZ REF LO ADF 2 400 Hz Ref Hi 400 Hz Ref Lo SN3500 E DATE COMMENTS 4A INITIAL RELEASE 780 MINOR DOC CHANGES COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY N LL a lt x N o B mc 5 9 a3 lt o dar Ow x Z 5 258 o O a A B D NOTES 1 SELECT APPROPRIATE SETUP DATA ON ADF INSTALLATION PAGE ANDEL Vista Ca itle A D F 2 2 reate Sunday 03 1998 Mod Sunday December 09 2007 Sheet 29 B D E DATE COMMENTS INITIAL RELEASE T Ai AR 780 MINOR DOC CHANGES c AVR 806 Correct KR22 SN3500 connection P2 to P1 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY EXTERNAL MARKER LAMPS IF INSTALLED MARKER RECEIVER SANDEL SN3500 NOTE 1 THESE LOAD RESISTORS ARE REQUIRED FOR PS ENGINEERING MARKER RECEIVERS EXTERNAL MARKER LAMPS IF INSTALLED MARKER RECEIVER KING KR22 SANDEL SN3500 NOTES 1 THESE LOAD RESISTORS ARE REQUIRED FOR PS ENGINEERING MARKER RECEIVERS RECOMMENDED FOR OTHER RECEIVERS TO PREVENT FAILURE OF THE SN3500 INDICATION IF THE ASSOCIATED MARKER LIGHT BULB FAILS 2 SET MARKERS TO ACTIVE
26. 3 1 c hlclem 3 1 3 1 1 Unpacking and Inspecting Equipment sess nennen nennen 3 1 3 2 Installation Considerations UU U U u uuu u u uuu 3 1 3 2 1 General Considerations ccccccccsseseescseeseescsesseeecaessesecaessesecaessesaesecaesaesecaesaesecaaaesecassaeaecaesaeaesasesateaees 3 1 3 2 2 Cooling Considerations iene rhe aee c Pe uhay o eed dec 3 1 3 2 3 Mechanical Installation Considerations L L L l s rennes 3 1 3 2 4 Electrical Installation Considerations I S 3 2 33 Signal Detaj S Ara aa 3 4 3 3 1 Connector P 1 Pinout Description U L a 3 4 3 3 2 Connector P 2 Pinout Descriptions l L L n n u 3 7 3 3 3 Connector P 3 Pinout Descriptions L L N L aaa 3 10 4 Setup Procedures 4 1 41 iuJpce E r 4 1 4 2 Accessing the Maintenance Menwus U ntn nnn ntn nini tn 4 1 43 Equipment Configuration Selections eee u u enne uuu 4 1 5 Operating Detalls ener tete ctae sss 5 1 6 Instructions For Continued
27. 806 429 TX OUT PIN CORRECTIONS P1 22 AND P1 7 REVERSED COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY NAV 1 AND ARINC 429 GPS INTERCONNECT KLN90 B SHOWN FOR REFERENCE NOTES 1 CONNECT OBS H FROM RECEIVER H or C WHICHEVER IS THE ACTIVE OUTPUT CHECK APPROPRIATE NAV RECEIVER SCHEMATICS CONNECT SIN OUT and COS OUT TO THE ACTIVE RETURN PINS USUALLY D F CONNECT OBS VREF TO EITHER STATOR RETURN PIN REF OR GROUND USUALLY E or G THE LOAD RESISTOR SIMULATES A SYNCHRO 2 THE APPROACH ACTIVE OUTPUT FROM THE GPS TO THE AUTOPILOT MAY HAVE TO BE AN ADDITIONAL RELAY SEE THE MANUFACTURERS INSTALLATION DIAGRAMS 3 THE PREFERRED INSTALLATION IS THE SN3500 P3 7 CONTROLLING AN EXTERNAL SWITCHING RELAY IF AN EXISTING SWITCH CONTROL BOX IS INSTALLED AND IT IS DESIRED TO LEAVE IT OPERATIONAL USE P3 4 TO SENSE GPS MODE AND SELECT SLAVE FOR THE MODE SETTING ON THE OBS RELAY CDI MAINTENANCE PAGE 1 MASTER SN3500 CONTROLS THE NAV GPS SWITCHING PREFERRED 2 SLAVE EXTERNAL NAV GPS SWITCH CONTROLS THE SN3500 4 CHECK MANUFACTURERS DOCUMENTATION FOR ANY ADDITIONAL INSTALLATION SPECIFIC RELAY POLES WHICH MAY ALSO BE NEEDED 5 KLN 90B PINOUTS SHOWN CERTAIN CONNECTIONS SUCH AS GPS DISPLAYED AND OBS LEG ARE SPECIFIC TO KLN 90B 6 MSG AND WPT ANNUNCIATORS ARE COMMUNICATED ON THE ARINC 429 SERIAL CHANNEL 7 FOR 3V COMPOSITE NAV SOURCES INSERT A 470K SERIES RESISTOR LOCATED AT THE SN3500 CONNECTOR NOT REQUIRED FOR 5V SOU
28. Accessories SPN Description 90143 SN3500 installation kit 90124 Bezel Adapter Kit KI 525 Flush Used to fill non standard sized hole in installations replacing a KI 525 indicator 90130 LK Lamp Kit Replacement lamp for lamp units 2 2 2 Bill of Materials SN3500 Install Kit SPN 32062 Description Conn D 15 with pins Positronics P N SD15F10JVLO 32063 Conn D 44 with pins Positronics PIN DD44F10JVLO 1 2 60144 Shim Flush Mounting 1 61062 Mounting Clamp 1 82005 IM Installation Manual SN3500 1 88114 USB Cable 1 2 3 Approval Summary 2 3 1 License Requirements None 2 3 2 Approval Data Technical Standard Order 82005 IM K TSO C113 Airborne Multipurpose Electronic Displays TSO C3d Turn and Slip Instrument TSO C4c Bank and Pitch Instruments 5 Direction Instrument Magnetic Gyroscopically Stabilized TSO C34e ILS Glide Slope Receiving Equipment Operating Within The Radio Frequency Range of 328 6 335 4 Megahertz TSO C35d Airborne Radio Marker Receiving Equipment TSO C36e Airborne ILS Localizer Receiving Equipment Operating Within The Radio Frequency Range of 108 112 Megahertz Sandel SN3500 Installation Manual Page 2 2 Technical Information TSO C40c VOR Receiving Equipment Operating within the Radio Frequency Range of 108 117 95 Megahertz MHz TSO C41d Airborne Automa
29. Altitude 100 Selected Course 1 114 Desired Track 115 Waypoint Bearing 116 Cross Track Distance 117 Vertical Deviation 125 Universal Time Coordinated UTC 147 Magnetic Variation 150 Time 251 Distance To Go 260 Date 261 GPS Discrete Word GAMA 266 FMC Nav Mode 275 Status Word GAMA 310 Present Position Latitude 311 Present Position Longitude 312 Ground Speed 313 Track Angle True 326 Lateral Scale Factor 327 Vertical Scale Factor 377 Equipment Identification 303 Message Length Type Num 075 Active Waypoint From To Data 074 Flight Plan Header 275 Status Word GAMA 113 Message Checksum 300 Station Type Class 304 Message Characters 1 3 305 Message Characters 4 6 306 Waypoint Latitude 307 Waypoint Longitude 82005 IM K 340 L R Procedure Turn Azimuth 335 L R Holding Pattern Azimuth 330 Arc Inbound Course 331 Arc Radius 332 Arc Change Angle Sandel SN3500 Installation Manual Technical Information Page 2 16 Technical Information 2 6 2 ARINC 419 429 Serial Transmitter Interfaces The SN3500 is capable of transmitting the following low or high speed ARINC 429 data LABEL DESCRIPTION Selected Course 100G Using extended SDI 320 Magnetic Heading 82005 IM K Sandel SN3500 Installation Manual Page 2 17 Installation 3 Installation 3 1 General 3 1 1 This section provides general suggestions and information to consider before installing the
30. Clarify composite input connection with analog NAVs Page 3 9 Clarify P2 10 HDG CRS Excitation connection when not connected Page 5 1 Added reference to 82005 PG SN3500 Pilot s Guide for light source identification and data color coding details Page 7 1 Updated INDEX maintenance page image Page 7 10 Updated GPS 1 maintenance page image Pages 7 10 amp 7 12 Added selections for ARINC 429 on GPS 1 and GPS 2 maintenance pages Page 7 11 Updated GPS 2 maintenance page image Pages 7 11 amp 7 12 Added selections for GPS Approach Mode Active Status on GPS1 and GPS2 maintenance pages Page 7 15 Added definition for lateral and vertical deviation output calibration in maintenance pages Page 7 18 KTA 810 configuration note added Page 7 19 Updated BRT DATA BLK maintenance page image Page 8 2 RTCA DO 160E Environmental Qualification Form added C1 12 16 05 11 17 2005 A R 824 Updated following pages Page iv revision Page 2 4 weight in kg Pages 2 6 and 3 5 deviation left right Pages 3 9 and 7 13 FCS selection Page 3 12 P3 10 NAV menu typo Pages 12 1 and 12 2 drawing rev updates Pages 1 33 amp 36 of installation drawings updated A R 806 amp A R 820 Updated for software version 2 01 version 3 00 and minor corrections Sample AFMS updated including FIS B weather N A Skipped 06 06 2005 A R 782 Minor doc changes for production release 05 06 2005 A R 782 Minor doc chang
31. DEVIATION INT RELAY Document Number Rev 82005 10 C reate Wednesday May 18 2005 Mod Sunday December 09 2007 Sheet 2 4 ANALOG GPS FCS LOC ENGAGE VERT FLAG VERT FLAG VERT UP VERT DOWN LAT FLAG LAT FLAG LAT LEFT LAT RIGHT TO FROM OBS OUT OBS RETURN OBS SIN OBS COS GPS DISPLAYED APPR ARM IN 8 FROM VHF NAV RECEIVER TO AUTOPILOT X H al Ego zsio dgu NI Ij ul z NI L uu m N 9915 1542 13 1453550 sur d HH 2 d P c g 3r 3 a oy ul gt l gt gt TO VHF NAV RECEIVER 220 Ohm PWR oe x Q l SN3500 P2 18 ILS1 ENERGIZE 6 GS Flag 36 GS Flag 22 GS Down 37 Nav Flag 23 Nav Flag 38 Nav Left 8 Nav Right P2 23 OBS RESOLVER H IN 37 OBS RESOLVER E VREF IN 8 OBS RESOLVER SIN OUT 38 OBS RESOLVER COS OUT P3 4 GPS1 SENSE 4 10 APPRARM OUT 3 POWER GROUND 15 GPS2 RELAY 7 GPS1 RELAY E DATE COMMENTS AT INITAL RELEASE C A R 806 MINOR DOC CHANGE P1 22 AND P1 7 REVERSED P2 37 WAS P2 7 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY BLOCK DIAGRAM SHOWS USE OF EXTERNAL AUTOPILOT SWITCHING RELAY USING SN3500 CONVENTIONAL LOW LEVEL INPUTS NOTES 1 I
32. H OR ACTIVE L ON ADF1 ADF2 MKR MAINTENANCE PAGE ANDEL Vista Ca MARKER BEACON 4 Document Number 82005 1 0 reate Sunday May 03 1998 Mod Sunday December 09 2007 Sheet 30 A B C D E COMMENTS SINGLE KING SERIAL DIGITAL DME USING KDI572 SINGLE KING SERIAL DIGITAL DME WITH SELF CONTAINED CONTROLLER COMMENTS INITIAL RELEASE At AR780MINORDOG CHANGES O o ANY KING SERIAL DME PERMISSABLE KN64 SHOWN FOR REFERENCE KN62 KN62A PERMISSABLE AATE MINOR DOC CHANCES SANDEL SN3500 NOTE 3 lt fe A R 806 ADDED ANALOG DME COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY KN 64 DME SANDEL SN3500 P2 E 6 Data Buss 4 36 Clock Buss 22 DME Request DME 1 Nav 2 Data Buss Clock Buss RNAV Request DME Common Data Buss Clock Buss DME Request DME 1 Hold Data Buss Clock Buss DME Request Data Buss Clock Buss DME Request DME Hold RNAV Request DME 1 Nav 2 NOTE 1 DME KDI 572 DME Common Data Buss Clock Buss RNAV Request DME Common Data Buss Clock Buss DME Request DME Hold RNAV Request NAV 1 Common NAV 2 Common Data Buss Clock Buss RNAV Request DME Common Data Buss Clock Buss RNAV Request DME Common NOTES 1 INA SINGLE DME CONFIGURATION THE SN3500 DETECTS BOTH DME HOLD AND NAV 1 NAV 2 ASSIGNMENT WHEN NAV 2 IS CHANNELED THE DME READOUT WILL ASSOCIATE WITH THE BEARING POINTER NAV 2 DUAL KING SERIAL DIGI
33. Inc ADDRESS 2401 Dogwood Wav Vista CA 92083 REVISION amp CHANGE NOS OF 00 160 Revision D Change DATE TESTED Nos 1 amp 2 From 06 04 ENVIRONMENTAL RICA DO Equipment Notes TESTS 160D Test SECTION Category Temperature amp Altitude 4 0 A2 F1 B PASS Temperature Variation combined Low Temperature 45 1 Ground Survival Operational High Temperature 4 5 2 amp 4 5 3 Ground Survival Operational Altitude 4 6 Decompression 4 6 2 Overpressure 4 6 3 In Flight Lossof Cooling 4 5 4 A2 Z PASS Humidity 6 0 A PASS Operational Shock and Crash Safety 7 0 B PASS Vibration 8 0 H R PASS RESO NANT FREQ UENC IES Section 8 7 2 Step a and d Pre Scan X 195Hz Y 500 2 2 160Hz Post Scan X 195Hz Y 450Hz Z 150Hz Section 8 8 1 3 Stepsa and e Pre Scan X 190Hz Y 425Hz Z 145Hz Post Scan X 190Hz Y 625Hz Z 145 2 Section 8 8 1 3 Steps b and d Pre Scan X 190Hz Y 390Hz Z 150Hz Post Scan X 190Hz Y 625Hz Z 150Hz Exploson 9 0 X Water proofness 10 0 x Fluids Susceptibility 11 0 x Sand and Dust 12 0 x Fungus 13 0 x Salt Spray 14 0 x Magnetic Effect 15 0 Z PASS Power Input 16 0 B PASS Voltage Spike 17 0 A PASS Audio Frequency Susceptibility 18 0 B PASS Induced Signal Susceptibility 19 0 B PASS Radio Frequency Susceptibility 20 0 WW PASS Radio Frequency Emission 21 0 M PASS Lightni
34. Kit and Accessories sse nennen nennen ennt 2 2 2 2 2 Bill of Materials SN3500 Install Kit L L L tette titt 2 2 2 3 Approval A 2 2 2 3 1 License Requirements o oe dee a ee a e a oe 2 2 2 3 2 Approval Data et e DR RR u b e ce pe e bert ee D ERR Re 2 2 2 3 3 Technical Standard Order Stipulation U l L nnne 2 3 2 3 4 Installation and Operational Approval Procedures U L nennen 2 3 2 4 Physical and Electrical Properties U 2 5 2 4 1 Physical Dimensions ll l l EE E AEE edad sS im baud 2 5 2 4 2 Summary Operational Characteristics U L u a 2 5 25 Connector SUMMay sect AAE NAA NEAN cate AEAEE EAA TE KAE AENEA EEAS RE 2 5 82005 IM K Sandel SN3500 Installation Manual Page iii 2 5 1 Connector PR aa tht A a eee Re ene e ANUS 2 6 2 5 2 Connector P2 dansk dull a ea ce Laeta ek ced eek aee mukuna et dies 2 9 2 5 8 Connector PS siti EET 2 12 2 5 4 Signal Characteristics Table u 2 13 2 6 ARING 429 ECCE 2 15 2 6 1 ARINC 419 429 Serial Data Receivers Interfaces U nnns 2 15 2 6 2 ARINC 419 429 Serial Transmitter Interfaces U 2 17 3 Installation H 3 1
35. OBS RELAY CDI MAINTENANCE PAGE SET OBS TYPE TO DIFF A ANDEL Vista Ca RESOLVER INTERCONNECT 82005 10 reate Thursday December 10 1998 Mod Sunday December 09 2007 Sheet 25 E DATE COMMENTS T A INITIAL RLEASE 780 MINOR DOC CHANGES COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY GPS SWITCH ANNUNCIATOR MATRIX GARMIN GARMIN I 150 250 GARMIN 155XL 300 KING KING MORROW 150XL 250XL 155 165 300XL KLN89 KLN90 SN3500 MAGELLAN TRIMBLE MSG ANNUNCIATORS WPT ACTV APPR ARM ARM APPR ACTIVE OBS LEG OBS HOLD PTK COMMANDS ARM CMD ARM CMD ARM CMD ARM CMD APPR ARM HOLD CMD HOLD CMD OBS CMD OBS or HOLD NOTES 1 USED ONLY ON GARMIN 155 165 WHICH REQUIRED LATCHED ARM COMMANDS 2 USED ON GARMIN AND KING RECEIVERS WHICH REQUIRE LATCHED MODE COMMANDS BUT NOT ON II MORROW RECEIVERS 3 SELECT APPROPRIATE RECEIVER ON THE SN3500 GPS MAINTENANCE PAGE IF INSTALLED RECEIVER IS NOT SHOWN ON THIS MATRIX USE NEAREST COMPATIBLE SETTING OF THE SAME MANUFACTURER AND INSURE THE TEXT AND COLORS OF THE ON SCREEN ANNUNCIATORS ARE ACCEPTABLE 4 MSG AND WPT ANNUNCIATOR DISCRETES ARE NOT REQUIRED WITH ARINC 429 RECEIVERS 5 GARMIN GNS 430 NOT SHOWN DOES NOT REQUIRE ANY DISCRETE ANNUNCIATOR WIRING SANDEL Vista Ca 02 SN3500 INSTALLATION DRAWING GPS SWITCH ANNUNCIATORS Document Number 82005 10 M reate Thursday June 18 1998 Mod Sunday December 09 207 Sh
36. RELAY SWITCH ANNUNCIATOR UNIT Document Number Rev CLAVE MODE ONIS CONNECT P3 4 OR P3 7 BUT NOT BOTH 82005 1 0 2 reate Tuesday April 28 1998 Mod Sunday December 09 2007 Sheet 22 THIS DIAGRAM SHOWS USE OF INTERNAL NAV CONVERTER AND FROM VHF NAV RECEIVER A R 780 MINOR DOC CHANGES GPS LORAN RECEIVER ERRER DEVIATION RELAY OF SN3500 or SN3500 KLN 90B SHOWN FOR opaca REFERENCE ded aan 3 Composite 1 In 3 ILS1 ENERGIZE APPR ACTIVE ro SEE NOTE 2 E TO VHF NAV KLN90 B SHOWN R CEIVER 5 6 SEE NOTE 5 RESOLVER g INTERCONNECT OBS RESOLVER H IN OBS RESOLVER E F VREF IN OBS RESOLVER SIN OUT OBS RESOLVER COS OUT 429 1 RX A 429 1 RX B ARINC 429 TX A ARINC 429 TX B 23 ARINC 429 RX A JUMPERS REQUIRED IFNO ARINC 429 RX B INSTALLED En x ARINC 429 RX A ARINC 429 RX B 429 1 TX A 429 1 TX B APPR ACTIVE 14 LRN APPR IN APPR ARM 44 LRN APPR ARM IN GPS DISPLAYED RELAY SENSE NOTE 8 GPS1 SENSE APPR ARM OUT OBS CMND OUT ARM SELECT LEG OBS CTRL IN SLAVE MODE THE RELAY DRIVE IS PART OF THE EXTERNAL SWITCH ANNUNCIATOR ap 144004 15 GPS2 RELAY UNIT MASTER MODE 4 GPS1 RELAY ko O 4 GPS SELECTED GPS ENABLED FROM SLAVE MODE gt SWITCH ANNUNCIATOR UNIT SLAVE MODE ONLY GPS SWITCHING RELAY CONNECTIONS SEE NOTE 3 CONNECT P3 4 OR P3 7 BUT NOT BOTH pp C A R
37. SWITCH ANNUNCIATOR UNIT SLAVE MODE ONLY GPS SWITCHING RELAY CONNECTIONS SEE NOTE 4 CONNECT P3 4 OR P3 7 BUT NOT BOTH 6 9 98 A E DATE REV COMMENTS A INITIAL RELEASE j _ A A R 780 MINOR DOC CHANGES BU PSPIN4RENAMED C A R 806 MINOR DOC CHANGE P1 22 AND P1 7 REVERSED P2 37 WAS P2 7 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY NAV 1 AND RS 232 GPS INTERCONNECT KLN89 B SHOWN FOR REFERENCE KX165 KNS80 KNS81 SWITCHING SEE NOTE 2 KX165 ONLY STATOR F O GROUND KNS80 KNS81 ROTOR Oo ONLY STATOR D NOTES 1 CONNECT OBS H FROM RECEIVER H or C WHICHEVER IS THE ACTIVE OUTPUT CHECK APPROPRIATE NAV RECEIVER SCHEMATICS CONNECT SIN OUT and COS OUT TO THE ACTIVE RETURN PINS USUALLY D F CONNECT OBS VREF TO EITHER STATOR RETURN PIN REF OR GROUND USUALLY E or G THE LOAD RESISTOR SIMULATES SYNCHRO 2 THESE CONNECTIONS FOR KX165 OR KNX80 81 PREVENT THE RECEIVER FROM FLAGGING THE NAV SIGNAL WHEN THE RESOLVER IS BEING USED BY THE GPS CONSULT THE APPROPRIATE KING DOCUMENTATION FOR FURTHER INFORMATION 3 SEE ARINC 429 INSTALLATION PAGE WHICH DOES NOT REQUIRE THE RESOLVER SWITCHING RELAY WHERE APPLICABLE SEP 4 TO SEIDEN SEEC EFT ME SEG HES EAC ANTEC PAGE 1 MASTER SN3500 CONTROLS THE NAV GPS SWITCHING PREFERRED 2 SLAVE EXTERNAL NAV GPS SWITCH CONTROLS TH
38. THE INSTALLED SWITCHING RELAYS WHEN NAV 2 IS CHANNELED THE DME READOUT WILL ASSOCIATE WITH THE BEARING POINTER NAV 2 SELECTION IF THE DME IS NOT DME2 HOLD RELAY DME2 HOLD ASSIGNABLE LEAVE THE CORRESPONDING PIN UNCONNECTED SET DME TO LO FR DME1 ON NAV ILS DME 2 MAINTENANCE PAGE ENABLE NAV2 DME DISPLAY 2 IN A DUAL DME CONFIGURATION THE SN3500 CAN ONLY DETECT DME HOLD IT ALWAYS ASSOCIATES DME 1 WITH NAV 1 AND DME 2 WITH NAV 2 ANDEL Vista Ca ARINC 568 Bl Document Number 82005 1 0 reate Sunday May 03 1998 Mod Sunday December 09 20dBheet 32 3 A B C SERIAL HEADING WX500 NOTES 1 2 RS232 TX SN3500 RS232 RX REMOTE CLEAR HDG CONFIG HDG CONFIG OPTIONAL REMOTE WX500 CONFIG GND CONFIG GND RS232 GND 35 WX RS 232 GROUND SYNCHRO HEADING REQUIRED FOR GNS430 NOTE 1 WX500 1 GARMIN 430 Hiec Oa HDG CONFIG P4001 RS232 Rx CONFIG GND CONFIG GND 7 RS232 GND 5 i 2 GARMIN 430 OPTIONAL REMOTE REMOTE CLEAR HDG CONFIG HDG CONFIG SN3500 WX RS232 2 RX RS 232 1 TX CONFIG GND CONFIG GND RS232 GND WX RS 232 GROUND 400 Hz Reference Sync Z HDG BootStrap X OUT HDG BootStrap Y OUT SEE MFG S INSTALL MANUAL FOR HEADING FLAG INTERCONNECT INVERTER 26 VAC Hi 26 VAC Lo D E DATE COMMENTS AT INITIAL RELEASE A R78 MNORDOCCHANGES B REVISED NOTES t INTEN
39. course sensing input of an AFCS When the Course Select rotates either direction passing 90 clockwise or counterclockwise from the lubber line of the SN3500 will generate an open drain closure An external relay may be required to make this signal active high P3 15 GPS2 Switching Relay Discrete Output 82005 IM K Can be used to operate a switching relay whenever GPS2 or Loran2 is selected by the NAV pushbutton The receiver type is selected on the LNAV 2 maintenance page Sandel SN3500 Installation Manual Page 3 12 Setup Procedures 4 Setup Procedures 4 1 General Setup procedures for the SN3500 are described along with the Maintenance Menu below The Maintenance Menu is accessed and addressed through the use of pushbuttons and the Selected Heading knob No external connector pin programming is required 4 2 Accessing the Maintenance Menus To access the Maintenance Menus perform the following operations A Prior to applying power to the SN3500 depress and hold the BRG and the MEM pushbuttons then apply power to the unit Continue to hold until the first maintenance menu appears This protocol insures that maintenance menus cannot be called up accidentally during flight B Once the Maintenance Menu is entered press the NEXT or PREV softkeys to cycle the MAINTENANCE MENU pages Use the UP DOWN arrow keys for selections and rotate the right knob to adjust and select On some menus additional soft key legends
40. figure Section 7 1 14 New Dimmer Control configuration Section 11 1 9 Added LOC GS deviation test Following sections renumbered Section 12 DWG 82005 10 sheet 41 N A Intentionally skipped 8 24 09 3 2 09 Updated for software version 4 01 AR1087 Section 3 3 1 change inverter range from 360 440Hz to 240 560 Hz Section 3 3 2 change inverter range from 360 440Hz to 240 560 Hz Section 7 1 1 corrected reference from ST3400 to SN3500 Updated for software version 4 00 AR1055 Page vi Updated revision history Section 1 2 1 Added Optional Reversionary Display Section 1 4 17 Added NVIS paragraph Section 1 4 18 New Reversionary Display paragraph Section 2 3 2 added TSO C3d and C4c Section 2 5 3 Added REV CNTRL Label to connector pin 6 Section 2 6 1 Added ARINC labels for Roll Pitch and Lateral Acceleration Section 3 3 3 Added Reversionary Control signal to connector P3 pin 6 Section 7 1 3 Updated compass maintenance page for Reversionary Attitude Section 7 1 4 Added TACAN 1 amp 2 Multi Channel selection Section 7 1 5 Added DME1 Multi Channel selection Section 7 1 6 Added DME2 Multi Channel selection Section 11 1 17 Added ground test procedure Section 12 Added 82005 41 to drawing list 8 26 08 Updated for software version 3 05 AR1032 Page 2 12 Assigned P3 13 to NVIS Control Page 3 12 Added NVIS P3 13 description Page 7 20 Modified Maint Page 14
41. included in the Appendix The basis of approval is for use as a primary navigation display for the functions of basic directional and navigational information Moving map operations of the SN3500 is to be approved as supplemental means for VFR or IFR navigation consistent with the approval of the long range navigation system See appropriate FAA Advisory Circular AC or other guidance on Loran C GPS FMS or INS for approval methods of such equipment Applicable Federal Aviation Regulations FAR must be adhered to 82005 IM K Sandel SN3500 Installation Manual Page 2 3 Technical Information Flight Standards Information Bulletin FSAW 95 09 Amended titled Electronic Horizontal Situation Indicator EHSI Approvals was originally published for the purpose of assisting Aviation Safety Inspectors with approval authority and methods for conducting a field approval for electronic HSI s This FSIB describes the qualification of displays intended for use as essential not critical to preclude the need to conducting additional testing to substantiate immunity to high intensity radiated fields HIRF requirements The Environmental Qualification Form for the SN3500 is included in the Appendix and should be referenced to the categories appropriate to the aircraft type and environment into which the SN3500 is to be installed The environmental category for the SN3500 should be stipulated on the FAA Form 337 or other approval form A Func
42. of the Course Pointer up For older Century autopilots a Datum Excitation 5Khz input is provided However an external transformer coupler must be fabricated See installation drawings GPS Annunciators For receivers without serial communication capability discrete annunciator inputs are provided for ARM ACT WPT or HLD MSG OBS LEG Mode and Parallel Track Connect the pins appropriate to the installed receiver and select the receiver type on the LNAV maintenance page See GPS SWITCH ANNUNCIATORS Installation drawing for the complete matrix of outputs and annunciators Discrete control outputs are provided for APPR ARM OBS Mode King KLN90 and HOLD II Morrow These are open drain outputs The Garmin GNS receivers use ARINC 429 for the annunciator functions so no discrete connections are used VLOC Navigation Internal NAV Converter For new installations that do not already have an external NAV converter the SN3500 supports internal demodulation of composite NAV and Localizer to supply the display and autopilot outputs with L R deviation and course selection See the appropriate installation drawings VLOC Navigation External NAV Converter 82005 IM K Sandel SN3500 Installation Manual Page 1 5 1 4 7 1 4 8 General Information The SN3500 has a single conventional set of low level analog inputs for deviation flags etc from a primary NAV receiver See the installation diagram for details These inputs are not u
43. or is 400Hz Excitation 40 Course Dai Out Locked to P1 16 or P2 10 26 Hdg Datum Out Locked to P1 16 or P2 10 11 Hdg X Out Out Bootstrap locked to inverter on P1 82005 IM K Sandel SN3500 Installation Manual Page 2 10 P2 Connector continued from previous page Technical Information Pin Name Signal Type dependent on maintenance page selection 41 Hdg Y Out Out Bootstrap locked to inverter on P1 27 FCS ILS Out Active Low Energize Out 12 FCS Lat Flag Out LL Out gnd ref 42 FCS Vert Flag Out LL Out gnd ref 28 FCS Lat Dev Out LL Out gnd ref RIGHT 13 FCS Vert Dev Out LL Out gnd ref UP 43 FCS Lat Out Superflag Out Superflag Out 29 FCS Vert Out Superflag Out Superflag Out 14 RS232 2 Out O R9292 44 Spare Out 30 429 A side 429 Out 18 TAB A429 B side 429 Note 1 For XYZ inputs Z is signal ground P1 1 For XYZ Outputs Z is power ground 82005 IM K 15 14 13 Qiu E 12 11 10 Ol 4027 4 4 bw 3 OF O O 30 29 28 27 26 25 24 23 22 21 20 19 18 Quo IOS 0S Or 0 20 20 Q Ov uo 44 43 42 41 40 39 38 37 36 35 34 33 32 31 Or Qr Q O Q Or Ore Os Q cQ OQ u 2 1 O O 17 16 O Outside View Mating Connector Sandel SN3500 Installation Manual Page 2 11 2 5 3 Connector P3 Technical Information Pin N
44. rN N FG X DG Y FG Y SIGNAL GROUND v v FG Z 400 Hz EXCITATION Synchro H Synchro C 3 USING KMT 112 FLUX GATE WITH A 26VAC INVERTER KMT112 FLUXGATE FGX INVERTER 9 LO A gif Ng 5l raz e 7 2v RMS NOMINAL 26 VAC LO N FG Ext Hi FG Ext Lo FG Excitation May be 2ea 1uF 35v Electrolytic back to back ANDEL Vista Ca itle i XYZ GYRO WITH KMT112 ize Document Number Rev B 82005 10 reate Wednesday May 18 2005 Mod Sunday December 09 2007 15 A B C D E DATE COMMENTS A INITITAL RELEASE LEAVING INSTALLED BUT BYPASSING THE SLAVING FUNCTION OF AIR 780 MINOR DOG THE COLLINS 328A 3G SLAVING ACCESSORY WHEN UPGRADING A Cl AF608 REVISED GYRO CONNECTIONS PN101 SYSTEM SEE NOTES COMPUER CONTROLLED DRAWING DO NOT REVISE MANUALLY NOTE 5 2200 1 8 w or larger 323A2G SN3500 P2 FLUXGATE 1 rex ao C rev C gg M ral E FG Ext Hi itati Y FG Excitation 24 O D FG ExtLo 328A 3G SLAVING AMP 19 GROUND NOTES EXCITATION 400HZ REF 16 GYRO FLAG 19 FLAG OUT GROUND SLAVING 3 THE 328A 3G PROVIDES A HEADING FLAG OUTPUT TO THE SN3500 SERVO SERVO SPIN MTR 115V 5 THE 2200 OHM RESISTORS ARE RECOMMENDED NOT REQUIRED TO REDUCE RINGING FROM THE INTERNAL INVERTER THE SN3500 APPLIES NO LOAD TO THE GYRO ERECT 26 VAC 1 THIS CONFIGURATION DOE
45. the average value of LOC reads 100 0 2 5 Exit the SN3500 maintenance page to the normal pilots LOC display On the test set remove both 90Hz and 150Hz simultaneously and verify the SN3500 display flags within 2 seconds On the test set select 155 DDM Left and verify that removing either tone individually will flag the SN3500 display within 5 seconds On the test set select 155 DDM Right and verify that removing either tone individually will flag the SN3500 display within 5 seconds Perform any other LOC performance tests desired 82005 IM K Sandel SN3500 Installation Manual Page 7 11 Appendix A Post Installation Procedures 7 1 6 Page 6 NAVALS DME 2 SANDEL 6 NAV ILS DME 2 CER E BRGJ MEM The NAV ILS DME2 page allows the selection of the NAV2 and DME2 sources Configuration Field Options Comment NAV NONE Selects NAV signal input 429 FR For 429 interfaces the standard setting 429H FR is TO Change to FR if the received 429 TO bearing information is from the VOR 429H TO station COMP NO BRG CAL Default 17 0 Only used when COMP is selected for the NAV signal input A VOR test set should be used to accurately calibrate the displayed bearing pointer reading ENRGZ NONE Selects ILS Energize input 429 429H ACTIVE H ACTIVEL 82005 IM K Sandel SN3500 Installation Manual Page 7 12 Appendix A Post Installation Procedure
46. when ILS Lockout is not disabled on the NAV maintenance page Connections to these pins are from the respective VHF navigation receiver and optionally by the GPS receiver The logic level of these inputs is selected on the NAV maintenance page and is normally active low P2 3 VHF NAV1 429A Composite P2 33 VHF NAV1 429B Primary 429 input from VHF NAV1 or composite input from analog receiver for VOR bearing pointer Composite is normally 5v VOR 33v LOC For 3V inputs a series resistor is required see the installation drawings When using the composite input for LOC deviation the calibration procedure found in section 7 1 5 must be followed for each specific LOC input 24 AWG shielded wire is recommended for these connections Note When using the composite signal for the localizer deviation input the calibration procedure found in section 7 1 5 must be performed after the installation prior to release for flight 82005 IM K Sandel SN3500 Installation Manual Page 3 7 Installation P2 4 2 AC X or AC DC SIN Input TACAN 1 429 419 A P2 34 ADF 2 AC Y or AC DC COS Input TACAN 1 429 419 B Inputs from ADF2 Receiver Selection of AC DC operation is on the ADF maintenance page For DC use P2 20 as the DC reference input For AC inputs Z is grounded 24 AWG twisted shielded pair wire is recommended for these functions 2 20 ADF2 DC Ref Used when DC Sin Cos inputs are used P2 5 ADF2 Valid Discrete ADF Valid input used if a
47. will be NAV2 redlined on the pilot s display when GPS1 NAV2 selected GPS2 NAV2 G1 G2 N2 82005 IM K Sandel SN3500 Installation Manual Page 7 20 Appendix A Post Installation Procedures NS GPS2 GPS2 Normal operation of sense lines as software version described above in Sense selections 3 00 and above When replacing a SN3308 with a NAV2 amp GPS2 SN3500 use this selection and NAV2 in Sense selections for installations with dual Garmin GNS Receivers where both receivers All four NAV sources are made available as NAV sources This is the sense input P3 5 for a relay which is wired to both the NAV 2 and GPS 2 relay outputs Ref SN3308 install manual 90106 IM G 4 dual Garmin install sheet 26 ILS LCK DISABLE Enables disables ILS Lockout feature ENABLE of the ILS input for NAV1 NAV2 LAT DEV n a Monitors FCS voltage outputs OFFSET n a Adjusts zero offset of the lateral deviation output VERT DV n a Monitors FCS voltage outputs OFFSET n a Adjusts zero offset of the vertical deviation output This adjustment may be used to fine tune the autopilot localizer or glide slope tracking if the SN3500 lat and vertical deviation outputs have been connected to the autopilot 82005 IM K Sandel SN3500 Installation Manual Page 7 21 Appendix A Post Installation Procedures 7 1 11 Page 11 WX 500 SANLDEL 11 WX 500 VALUE R VOLT V PINS FUNC N A v
48. 0 Installation Manual Page 11 16 11 5 3 11 5 4 11 5 5 82005 IM K Appendix E Checkout Procedures For each NAV source verify proper operation of the flight control system both in NAV coupled mode and in heading mode Completed Comment Verify proper operation of the WX 500 Stormscope sensor if installed Completed Comment GPS Approach Operations If installed configure each approach capable GPS receiver for a non precision approach Conduct the approach and evaluate proper operation of CDI sensitivity and deflection e Resolver interface in OBS or HOLD mode e GPS annunciator display on the SN3500 as installed e External GPS mode control switches on the SN3500 as installed e Waypoint display when map is enabled on the SN3500 Completed Comment TACAN Approach Operations If installed conduct at least one TACAN approach in VFR conditions Conduct the approach and evaluate proper operation of e CDI sensitivity and deflection Completed Comment ILS Approach Operations Conduct at least one fully coupled ILS approach in VFR conditions for each VHF NAV receiver installed During the approach verify proper operation of e Lateral deviation display CDI in both ARC and 360 modes e Vertical deviation display in both ARC and 360 modes Sandel SN3500 Installation Manual Page 11 17 11 5 6 82005 IM K Appendix E Checkout Procedures e Marker beacon annunciation on the SN3500 if installed
49. 00 Primary Navigation Display Add following text if Data Link Weather is installed The FIS B weather display shall not be used for tactical maneuvering of the aircraft SECTION Ill EMERGENCY PROCEDURES If the SN3500 fails to operate use the magnetic compass as a heading source Sandel SN3500 Installation Manual Page 10 1 82005 IM K Appendix D Sample Airplane Flight Manual Supplement If the remote directional gyro DG becomes inoperative the magnetic fluxgate will provide the heading and the resulting heading display will respond much more slowly than normal The compass rose changes color from white to amber and digital heading numbers will be redlined If the fluxgate fails the SN3500 Navigation Display will continue to display heading based on the directional gyro DG input The compass rose changes color from white to amber heading numbers will be redlined Add following text if FCS outputs are Used If the FCS FDBCK ERR message appears when in autopilot coupled NAV or APPR mode immediately monitor the lateral and vertical deviation indicators If they are not tracking properly immediately disable the autopilot and flight director NAV or APPR mode for the duration of the flight HDG mode may still be used if the autopilot tracks the SN3500 HDG bug properly Add following text if FCS outputs are not used If the FCS FDBCK ERR message appears it has no effect on the autopilot system and no pilot action needs to
50. 3500 Interconnect Wiring Diagrams for detailed wiring information and appropriate notes Refer to the Functional Pinout Descriptions for explanations of pin functions A The installing agency will supply and fabricate all wiring harnesses The length and routing of wires must be carefully measured and planned before the actual installation is attempted Avoid sharp bends in the harness or locating the harness near aircraft controls Observe all recommended wire sizes and types and subscribe to appropriate FAR Parts 23 25 27 and 29 as well as AC 43 13 1 and 2 B The use of MIL C 27500 shielded wire and MIL W 22759 single conductor wire is recommended The use of ferrules or grounding blocks for signal ground and digital ground returns is satisfactory however each ground return must be electrically separated C When an existing installation of a navigation source selection relay unit is installed to provide mode control switching and annunciation for a GPS or other long range navigation system the SN3500 may not perform these functions simultaneously This does not preclude the SN3500 from annunciating such mode control functions D In order to ensure optimum performance the SN3500 and associated wiring must be kept at least a minimum of three feet from high noise sources and not routed with cables from high power sources E Prior to installing the SN3500 a point to point continuity check of the wiring harness should be accompl
51. 7 Synchro Y Z grounded 19 ILS Energize2 In Discrete In Discrete Valid Discrete Open Gnd or Open 28Vdc In A429 A side 429 4 na a A419 A side 419 TACAN only DC Sin DC Sine ADF only A407 Synchro X Z grounded In A429 B side 429 34 Barts A419 B side 419 TACAN only DC Cos DC Cosine ADF only A407 Synchro Y Z grounded In 20 ADE 2 DC Ret ADF Ref ADF DC Note Not used when 429 or XYZ is data source z In 3 Valid Discrete Valid ADF Discrete Note Not used when 429 is data source In A429 Aside 429 RS422 side 422 35 RS232 Ground side A710 Composite Video In Note For composite inputs see P2 42 A429 B side 429 2 RS422 side 422 RS232 Rx 82005 IM K Sandel SN3500 Installation Manual Page 2 9 P2 Connector continued from previous page Technical Information Pin Name Signal Type dependent on maintenance page selection In 6 DME 1 DATA A568 Analog DC In 36 DME 1 CLK A568 Analog DC In 22 DME 1 SYNC A568 7 DME 1 Hold n Discrete Valid 37 OBS Resolver In DC Ref Resolver DC In 23 OBS Resolver H Resolver H 8 OBS Resolver Out X Sin out Resolver Out 38 OBS Resolver Out Y Cos out Resolver Out 24 Fluxgate In Excitation Fluxgate Excitation 9 Fluxgate X In 39 Fluxgate Y 25 Fluxgate Z Gnd In 3 inverter input used specifically if autopilot inverter is not 10 Hdg inverter connected P1 16
52. 9 GPS INT RELAY 82005 10 pp 24 B NAV 2 GPS2 RS232 82005 10 pp 25 B RESLOLVER INTERCONNECT 82005 10 pp 26 A1 GPS SWITCH ANNUNCIATORS 82005 10 pp 27 C SINGLE SN3500 GNS430 530 82005 10 pp 28 D1 SINGLE SN3500 DUAL GNS430 530 82005 10 pp 29 Ai ADF 82005 IM K Sandel SN3500 Installation Manual Page 12 1 Appendix F List of Effective Drawings and Attachments Drawing Rev Title 82005 10 pp 30 C MARKER BEACON 82005 10 pp 31 C DME KING SERIAL 82005 10 pp 32 A1 DME ARINC 568 82005 10 pp 33 C1 WX 500 82005 10 pp 34 C TCAS TRAFFIC 82005 10 pp 35 C TCAS Il 82005 10 pp 36 C1 SINGLE SN3500 GNS480 82005 10 pp 37 E WSI Data Link Receiver 82005 10 pp 38 B SN3500 with SG102 ARINC 429 or 407 Interface 82005 10 pp 39 A SN3500 with TACAN 82005 10 pp 40 A NVIS Control 82005 10 pp 41 B Reversionary Attitude Control 82005 IM K Sandel SN3500 Installation Manual Page 12 2 e 0 e e e e e ec e cec e cecoecococo 1 ee UT IT 1 L J e ececececececececoec cec ecoec oeceoeceo 9 1 614 e a e 0 5 1 e LEFT SIDE VIEW 00 o 9 9 9 98 9 9 3 285 QOO VO OO 9 C c elec 6
53. 9900BX ARINC 429 TX A ARINC 429 TX B ee D E DATE COMMENTS __ A R80INITIAL RELEASE COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SKYWATCH HP SN3500 GOODRICH SKYWATCH HP ARINC 429 TX A ARINC 429 TX B ON OFF CONTROL GROUND SKYWATCH HP SETUP TEST ALT DISPLAY TYPE STANDARD TCAS 791 A SETUP STBY OPER TYPE 5 DISPLAY TYPE SET TO GROUND ARINC735 TYPE II SKYWATCH 497 SN3500 GOODRICH SKYWATCH 497 ARINC 429 TX A ARINC 429 TX B TEST SKYWATCH 497 SETUP ALT DISPLAY TYPE ARINC 735 STBY OPER TYPE GROUND NOTES 1 SEE MANUFACTURERS INSTALLATION MANUALS FOR COMPLETE WIRIING INTERFACE 2 TRAFFIC INTERFACE REQUIRES SN3500 SOFTWARE 2 01 OR HIGHER AND PURCHASE OF KEY CODE 3 SWITCHES REQUIRED IF SN3500 IS PRIMARY DISPLAY ANDEL Vista Ca 4 THE SN3500 MAY BE USED AS A SOURCE OF MAGNETIC HEADING Ws IF REQUIRED BY THE TCAS PROCESSOR REFER TO COMPASS TCAS TRAFFIC BOOTSTRAP DRAWING FOR INTERFACE Document Number 82005 10 reate Thursday November 06 2003 Mod Sunday December 09 2007 Sheet 34 E A B DATE COMMENTS C A R806 INITIAL RELEASE eee E NEUES INE COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SN3500 COLLINS HONEYWELL HONEYWELL TCAS II P1 TCAS 4000 CAS 67 CAS 81 TCAS 429 In A 31 TCAS 429 In B 17 RMP 7C P1B 30 RMP 7C 429 OUT A RMP 7D P1B 16 RMP 7D 429 OUT B NOTE 1 SEE MANUFACTURERS I
54. ACAN Use the BRG and MEM keys to select the character and the MAP and TFC keys to move the cursor TCN1 NONE Selects type of TACAN signal input If 429 bearing indication is off by 180 change 429H selection to opposite polarity 429 MC 429H MC XYZ XYZ 419 VALID NONE Not shown unless XYZ or XYZ is HIGH selected for TACAN source TCN2 NONE Selects type of TACAN signal input If 429 bearing indication is off by 180 change 429H selection to opposite polarity 429 MC 429H MC XYZ XYZ 419 VALID NONE Not shown unless XYZ or XYZ is HIGH selected for TACAN source MARKERS NONE Selects type of input from the marker ACTIVEL beacon receiver ACTIVE H 429 429H THOLD Default 003 Used to adjust the signal voltage threshold when ACTIVE L or ACTIVE H is selected for the marker beacon input 82005 IM K Sandel SN3500 Installation Manual Page 7 8 7 1 5 Page 5 NAVALS DME 1 SANDEL 5 NAV ILS DME VALUE R R VOLT V PINS FUNC N A v T F 19 w X CER BRG Appendix A Post Installation Procedures The NAV ILS DME1 page allows the selection of the NAV1 and DME1 sources Configuration Field Options Comment NAV NONE Selects NAV signal input 429 TO For 429 interfaces the standard setting 429H TO is Change to FR if the received 429 FR bearing information is from the VOR 429H FR station COMP NO BRG CAL Default 17 0
55. ANGES REMOVED NON GYRO COMPONENTS GYRO Z PIN CORRECTED COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SANDEL SN3500 XYZ GYRO Self Slaved FGX FG Y FGZ Synchro H 400 Hz EXCITATION Synchro C INVERTER NOTE 1 26 VAC HI 26 VAC LO NOTES 1 SELECT NONE FOR FLUXGATE TYPE S AN DEL Vista Ca itle XYZ GYRO GYRO SELF SLAVED ize Document Number Rev B 82005 10 reate Friday September 22 2000 Sheet 13 E DATE COMMENTS B INITIAL RELEASE COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY TYPICAL XYZ DG AND 26VAC FLUX GATE USING THE SN3500 INTERNAL FLUXGATE SN3500 NN NOTE 1 FG X FG X FG Y FG Y FG 2 FGZ FG Excitation FG Ext Hi FG Ext Lo XYZ GYRO DG X 3 DG Y SIGNAL GND GYRO VALID GYRO VALID EXCITATION GROUND 400HZ REF 26VAC 400HZ HI 26 400HZ LO NOTES 1 ANY TSO D XYZ FLUX GATE IS PERMISSABLE INSTALL ACCORDING TO MANUFACTURERS RECOMMENDATION IF FLUX GATE REQUIRES LESS THAN 26VAC USE A PAIR OF SERIES RESISTORS 2 WATT ONE IN EACH DRIVE LEAD TO PROVIDE THE CORRECT DRIVE VOLTAGE AN DEL Vista Ca itle XYZ GYRO Document Number Rev 82005 10 reate Wednesday 18 2005 Mod Sunday December 09 2007 Sheet 14 A B C D E DATE COMMENTS 806 TYPO P1 16 WAS 1 4 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SANDEL SN3500 XYZ GYRO Unslaved DG X
56. ATE Y FLUXGATE Z SIGNAL GROUND FLUXGATE EXCITATION STEPPERA STEPPER C GYRO VALID GROUND PER MFG S INSTALL MANUAL AVIONICS BUS t P L a Y c L n Fluxgate X 112 Fluxgate Fluxgate Z Exc H Exc C FV DRIVE KG102 GND GYRO MOTOR A MOTOR C GYRO VALID GND AUTO MAN CW MAN CCW POWER GND E INITIAL RELEASE PAAR 780 MINOR DOC CHANGES REMOVED NON GYROITEMS COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY ANDEL Vista Ca itle KING KG102A SN3500 SLAVING Es Document Number 82005 1 0 reate Friday September 22 2000 Sheet 10 A B C D E DATE COMMENTS B INITIAL RELEASE COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY BENDIX KING KI525A BOOTSTRAP MASTER WITH NO INTERNAL SN3500 SLAVING NOTES 1 AND 2 SN3500 525 DG X DG Y SIGNAL GND EXCITATION GROUND GYRO VALID GYRO VALID A C 26VAC 400HZ HI 26VAC 400HZ LO 1 SELECT NONE FOR FLUXGATE E THIS CONFIGURATION IS USED WHEN BOOTSTRAPPED FROM AN EXISTING KCS55 SLAVED COMPASS SYSTEM THIS MIGHT BE DESIRED WHERE AN EXISTING IS MOVED TO THE COPILOTS SIDE AND AN SN3500 IS INSTALLED ON THE PILOTS SIDE UNDER THIS CONDITION THE SN3500 CAN BE DRIVEN BY THE BOOTSTRAP OUTPUT OF THE COPILOTS HSI ANDEL Vista Ca e A KCS55 BOOSTRAP XYZ Size Document Number Rev reate Wednesday May 18 2005 Mod Sunday December 09 2007 Sheet 11
57. Airworthiness u 6 1 6 1 lcge 6 1 7 Appendix A Post Installation Procedures 7 1 7 1 1 Page T INDEX iis sist M 7 2 7 1 2 Page 2 SY Aca ci 7 3 7 1 3 Page 9 COMPASS SYSTEM ai ioeie nre cate tn koe e i D y Dn nga 7 4 7 1 4 Page 4 ADE TAGANF MIKR uu a a ct ca ee tea he o nen ve reU c naa 7 7 7 1 5 Page NAV IES DMBE 1 ttt ni cente centi tid cnr nece e 7 9 7 1 6 Page 6 NAV IES DME 2 ii cr etd e tena nae er aee er 7 12 7 1 7 E w mus ba hukaq ak E Q apa aaa oaa 7 14 7 1 8 Page 62 0PO22 u sa uya awakuy phu ua u taba eRe ee 7 16 7 1 9 Page 9 FCS EMULATION I ull ttn tt cite tenta tn e 7 18 73 10 Page 10 OBS RELAY 7 CDI tn tet an id e 7 20 Tik WX M 7 22 73 12 12 LTaffl 5 uama e en upa Gertie 7 23 743 Page 19 STATUS 2 e ir e e Rachie eren irre eed 7 24 74 14 Page 14 BRIDATA rtt tn teer ente hene reor de aee Qu cr 7 25 Page 15 POWOLD ederet ede aet eda ep efr er d 7 27 82005 IM K Sandel SN3500 Installat
58. DITIONAL TEXT TO EMPHASIZE SN3500 input power requires 11 to 33 VDC POWER REQUIREMENTS MODIFIED NOTE 2 TO INCLUDE CLARIFICATION FOR AUTOPILOT CONNECTION See Note 4 Sam 5 5 UPDATED FOR 14 VOLT AIRCRAFT AND j NOTE 4 AR 1023 COMPUTER CONTROLLED DRAWING SANDEL SN3500 DO NOT REVISE MANUALLY 5 AMP ACFT POWER 14 28 VDC AVIONICS BUS o ACFT POWER aa PIRATE fy aso n ME POWER GROUND 26VAC 400HZ MAIN INVERTER 26VAC 400HZ SECONDARY INVERTER NOTES 1 USE 20AWG WIRE BOTH GROUNDS AND BOTH POWER LEADS REQUIRED 2 INVERTER 1 ONLY REQUIRED IF XYZ GYRO OR XYZ ADF ARE CONNECTED TO P1 OR IF BOOTSTRAP SYNCHRO OUTPUT IS CONNECTED OR IF AUTOPILOT USES AC COURSE AND HEADING DATUM AND CRS HDG EXTERNAL EXCITATION P2 10 IS NOT USED 3 INVERTER 2 ONLY REQUIRED IF XYZ ADF IS USED CONNECTED TO P2 4 INSTALLATIONS IN 14 VOLT AIRCRAFT REQUIRE 533500 SERIAL NUMBER 5 2500 OR HIGHER SN3500 SERIAL NUMBERS LOWER THAN 5 2500 AND INSTALLED IN 14 VOLT AIRCRAFT REQUIRE A 14V TO 28V CONVERTER CONTACT SANDEL FOR COMPATABLE MODELS ANDEL Vista Ca POWER AND INVERTER 0177 77 82005 10 03 1998 Mod Wednesday July 23 2008 5 1 E DATE COMMENTS __ B INITIAL RELEASE G A R 806 Minor change corrected signal ground line Corrected pinout for excitation and autopilot signal BLOCK DIAGRAM SHOWS USE OF INTERNAL AUTOPILOT SWITCHING RELAY names
59. E SN3500 5 CHECK MANUFACTURERS DOCUMENTATION FOR ANY ADDITIONAL INSTALLATION SPECIFIC RELAY POLES WHICH MAY ALSO BE NEEDED 6 FOR COMPOSITE NAV SOURCES INSERT A 470K SERIES RESISTOR LOCATED AT THE SN3500 CONNECTOR NOT REQUIRED FOR 5V SOURCE 7 ONLY USED WHEN SN3500 IS INMASTER MODE SELECT GPS1 FOR SENSE ON OBS RELAY CDI MAINTENANCE PAGE ANDEL Vista Ca NAV 1 RS 232 GPS EXT RELAY id Document Number 82005 1 0 reate Tuesday April 28 1998 Mod Sunday December 09 2007 Sheet 20 A B C D FROM VHF NAV RECEIVER 6 9 08 E DATE REV COMMENTS A INITIAL RELEASE P prac a THIS DIAGRAM SHOWS USE OF INTERNAL NAV CONVERTER AND T Ai A R780 MINOR DOG CHANGES 5 3 SE DEVIATION RELAY OF SN3500 6 WRROSMNORDOCCHANGEPTEEANDETT eS x s 2 FOR AUTOPILOT INTERCONNT SEE PAGE FCS DEVIATION INTERNAL RELAY m ADDED ANALOG DEVIATION CONNECTIONS GPS LORAN RECEIVER 7448 _NOTES SNS900 KLN89 B SHOWN FOR 470K DO NOT REVISE MANUALLY REFERENCE VAN cD Composite 1 In ILS1 ENERGIZE FCS LOC ENGAGE O GS Flag KX165 KNS80 KNS81 SWITCHING SEE NOTE 2 GS Flag ROTOR GS Up KX165 GS Down ONLY STATOR F O 33K I LAT FLAG Nav Fla g I 3 LAT LEFT Nav Left KNS80 KNS81 ROTOR H V I C
60. Excitation for items on connector P1 1 Shield Gnd In A429 A side 429 81 TEASTA RS422 side 422 RS232 Ground side In A429 B side 429 u iene 16 RS422 side 422 RS232 Rx In Datalink 1A 4429 A side 429 In 32 Data link 1B A429 B side 429 18 N C In A429 A side 429 Hdg1A A407 Synchro X Z grounded Stepper A Bendix King stepper Phase A In A429 B side 429 98 Hdg1B A407 Synchro Y Z grounded Stepper C Bendix King stepper phase C In 19 Hdg Valid Discrete Valid Analog Note Not used when 429 is data source In A429 A side 429 4 CANA A419 A side 419 TACAN only DC Sin DC Sine ADF Only A407 Synchro X Z grounded In A429 B side 429 SASS B side 419 TACAN only DC Cos DC Cosine ADF Only A407 Synchro Y Z grounded In 20 ABET DG Ref ADF Ref ADF DC Note Not used when 429 or XYZ is data source In 9 ADFA Valid Discrete Valid ADF Discrete Note Not used when 429 is data source In A429 A side 429 39 95422 side 422 RS232 Ground side In A429 B side 429 a WX900 1B RS422 side 422 RS232 Rx 82005 IM K Sandel SN3500 Installation Manual Page 2 6 Technical Information P1 Connector continued from previous page Pin Name Signal Type dependent on maintenance page selection In Differential pair to pin 36 6 GS1 LL Flag In Flag Note For use with external SUPERFLAG see installation drawing for series resist
61. G NAV FLAG FROM VHF NAV NAV FLAG GND DC COURSE CRS ERROR NOTE 2 TOFCS DC HEADING HDG ERROR DC CRS HDG REF GND HDG CRS REF jo mz SIGNAL GND GS FLAG GS FLAG GS DEV UP GS DEV DOWN GS FLAG FROM VHF NAV GS FLAG GS DEV UP GS DEV DOWN HDG VALID HDG VALID GYRO VALID ome COURSE DATUM HDG DATUM HDG VALID RESOLVER H OBS H RESOLVER C RESOLVER D RESOLVER E FROM VHF NAV RESOLVER F 30HZ ONLY RESOLVER G OBS COS OUT OBS DC REF SEE NOTE 3 lo o lt lt x NOTES 1 THE SYSTEM 400HZ INVERTER WILL NORMALLY BE CONNECTED TO THE HEADING SYNCHRO H TERMINAL THIS WIRE CAN BE USED TO DRIVE THE SN3500 REFERENCE INPUT IN AN UNUSUAL CASE THE SYNCHRO MIGHT HAVE BEEN WIRED IN UPSIDE DOWN AND THE 400HZ REFERENCE MAY BE ON THE C TERMINAL 2 IF AN EXISTING CONVERTER IS INSTALLED SUCH AS A KA 52 OR KA 57 LEAVE UNIT INSTALLED AND SELECT KI525 ON FCS EMULATION PAGE 2 3 SHOWN IS THE 30HZ RESOLVER INTERCONNECT CHECK APPROPRIATE NAV RECEIVER SEE NOTE 1 HDG CTH HDG CT C HDG CT X FROM INVERTER De ere OUTPUT TO HDG CT Z SYNC X OUT SYNC Y OUT Hk lo OUTPUT TO SYNCHRO 400HZ REF DRIVE MOTOR 1 DRIVE MOTOR 2 DRIVE MOTOR 3 DRIVE MOTOR 4 SLAVING CT H SLAVING CT C KMT112 FG DRIVE MOTOR 1 DRIVE MOTOR 2 DRIVE MOTOR 3 DRIVE MOTOR 4 SLAVING CT H SLAVING CT C SLAVING CT X SLAVING CT Y SLAVING CT Z STEPPER A STEPPER C
62. GPS is ANALOG selected from list below SERIAL VERT ENA NONE Automatically configured when GPS is ACTIVE H selected from list below ACTIVE L SERIAL OBS CAL DEFAULT 0 0 Automatically configured when GPS is selected from list below May require adjustment if the GPS receiver uses an RS 232 interface and has a resolver connected ARINC 429 429 Not shown when selected GPS does 429H not have ARINC 429 output 82005 IM K Sandel SN3500 Installation Manual Page 7 14 Appendix A Post Installation Procedures APR ACTV NONE GPS approach active source select ANNUN IN ACTIVE L ACTIVE H GPS Select from list Select the appropriate model of GPS from the list Press the SET soft key CLR button to program 82005 IM K Sandel SN3500 Installation Manual Page 7 15 7 1 8 Page 8 GPS2 ee VAN IN BB 825359222 H F w X R A uc 4 gt Appendix A Post Installation Procedures me CER j BRG MEM The GPS2 page allows the selection and configuration of the GPS2 input Configuration Field Options Comment ANNUN NONE Automatically configured when GPS is ACTIVEL selected from list below SERIAL LAT DV NONE Automatically configured when GPS is ANALOG selected from list below SERIAL VERT DV NONE Automatically configured when GPS is ANALOG selected from list below SERIAL VERT ENA NONE Automatically configured when GPS is AC
63. GROUND C BACK COURSE OR Y AS SHOWN IN SOME CASES C MAY BE SIGNAL AND H MAY BE GROUND CALL FACTORY WITH ANY QUESTIONS 4 WHEN BC OUTPUT NOT REQUIRED LEAVE UNCONNECTED 5 BC OUTPUT IS AN OPEN COLLECTOR RELAY REQUIRED IF BACK COURSE INPUT TO AUTOPILOT REQUIRES 28V TO ACTIVATE OTHERWISE CONNECT SN3500 BC OUTPUT DIRECTLY TO AUTOPILOT BC INPUT INVERTER EXC INVERTER 6 IF CRS HDG WORK BACKWARDS EITHER a USE OPPOSITE PHASE OF SIGNAL GROUND AC EXCITATION SOURCE b CHANGE LEFT RIGHT DATUM SETTING ON FCS EMULATION MAINTENANCE PAGE 26VAC 400Hz FROM 1 INVERTER or AUTOPILOT EXITATION 400 Hz to 5 KHz amp SANDEL vista 2200 6113500 INSTALLATION DRAWING te ECS GENERIC CRS HDG DATUM g Document Number 82005 10 reate Monday May 04 1998 Mod Sunday December 09 2007 Sheet 4 A B D E DATE COMMENTS A INITIAL RELEASE A R780 MINOR DOC CHANGES C A R 806 Minor change added connection for autopilot exitation COMPUTER CONTROLLED DRAWING m DO NOT REVISE MANUALLY 2 4 5 5 8 9 a n lt lt M4D AUTOPILOT sEE NOTE 1 SN3500 SEE NOTE 3 0838 HDG DATUM AC HDG DATUM 1 34 HDG DATUM LO AC CRS DATUM 10k CRS SIG CRS DATUM HI T E 27 CRS DATUM LO 10K 10K 3 HDG CRS DATUM EXITATION 0 EXITATION SIGNAL GND 26VAC 400Hz FROM 1 INVERTER or AUTOPILOT EXITATION 400 Hz to 5 KHz FCS 810 AUTOPIL
64. L Vista Ca itl MID CONTINENT 4305 reate Wednesday October 18 2000 Mod Sunday December 09 2007 Sheet 17 E COMMENTS INITIAL RELEASE A R 806 MINOR DOC CHANGE COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY DA XYZ COMPASS BOOTSTRAP OUTPUT NOTE 1 SN3500 Synchro X Synchro Y Synchro Z Inv Ref Hi Inv Ref Lo TO BOOTSTRAP SYNCHRO IN ELECTRONIC LOADS ONLY 26 VAC Out HI 26 VAC Out LO 429 HDG OUTPUT NOTE 10Hz output rate SN3500 429 OUT A 30 HEADING LABEL 320 429 OUT 15 7 1 1 SELECT NORMAL OR REVERSE FOR BOOTSTRAP SETTING ON FCS EMULATION PAGE S ANDEL Vista Ca Category SN3500 INSTALLATION DRAWING SN3500 COMPASS BOOTSTRAP reate Monday September 25 2000 Mod Sunday December 09 2007 Sheet 18 itle A B C D E DATE COMMENTS A INITIAL RELEASE 780 MINOR DOC CHANGES COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY DOTTED AREA REPRESENTS THE SN3500 INTERCONNECT THE BALANCE OF THE DATA IS SHOWN FOR REFERENCE SN3500 RIGHT LEFT RIGHT LEFT TO FROM TO FROM AN lc 3 o KG102 LIGHTING HI DIRECTIONAL LIGHTING CT GYRO LIGHTING HI 414v NAV PWR 428v NAV PWR 15v 15v 15v 15v 5v 45v 415v UNREG 415v UNREG SIGNAL GND SIGNAL GND DIGITAL GND DIGITAL GND PWR GROUND PWR GROUND AIRCRAFT GND Ixl5I I t lt lro zr NAV FLAG NAV FLA
65. L LAT DEV ANALOG NAV SELECT NAV COMP ENRGZ ACTIVE L LOC DV ANALOG GS DV ANALOG RELAY MODE MASTER SENSE GPS1 3 THE INSTALLER IS RESPONSIBLE TO INCLUDE IN THE AFMS THE FOLLOWING TEXT DME ARCS AND HOLDING PATTERNS WILL NOT BE DISPLAYED ON THE SN3500 EHSI 4 IN THIS CONFIGURATION A RELAY SENSE ERROR WILL BE DISPLAYED ON THE SN3500 WHEN THE GNS480 IS SET TO NAV AND THE SN3500 IS SELECTING GPS1 SANDEL vista SINGLE SN3500 GNS480 ize Document Number B 82005 10 Mod Sunday December 09 2007 Sheet 36 5 4 3 2 1 DATE REM COMMENTS j WSI Recei eS eceiver with SN3500 as sole display device 1D Added WSI AV 300 350 connections E Correct pin s AV 300 350 TX and Ground AR tbd COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SN3500 WSI INFLIGHT RECEIVER AV 200 2 AV 300 350 RS232 RX RS232 TX GND 2 s D 429A IN GND Note WSI mode must be set to No Flow Control See WSI manual for instructions WSI Receiver with SN3500 as secondary display device listen only WSI INFLIGHT RECEIVER SN3500 AV 200 VU 300 350 RS232 TX 32 429B IN GND E 2 429A IN GND ANDEL Vista Ca WSI Data Link Receiver WSI Data Link Receiver Document Number 82005 1 0 reate Friday October 28 2005 Mod Wednesday August 27 2008 Sheet 37 itle 1 COMPUTER CONTROL
66. LED DRAWING DO NOT REVISE MANUALLY SN3500 ARINC 429 HEADING INTERFACE SG102 P1 P1 s HDG1B ARINC 429 33 1 2 429 B OUT SHIELD GND 1 NOTES UNLESS OTHERWISE SPECIFIED 1 Unless otherwise noted all signal wiring is 22 to 24 AWG SN3500 ARINC 407 SYNCHRO SG102 HEADING INTERFACE HDG1B ARINC 40733 5 Y OUT C XL Nun V S INVERTER EXC 16 9 SHIELD GND 1 SANDEL Vista Ca 20 613500 INSTALLATION DRAWING itle SN3500 with SG102 ARINC 429 or 407 Interface Document Number Rev B 82005 10 reate Sunday December 09 2007 Sheet 38 1 DATE COMMENTS 18 JUL 08 INITIAL RELEASE AR 1023 gt a COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY ARINC 429 419 TACAN SN3500 TACAN 1 TACAN 1 4 rN N 429 419 A OUT Th ORME 54 s Urs pO SHIELD GND 1 GND TACAN 2 a ee y gt scale eT TACAN 2B 34 v 429 419 B OUT SHIELD GND 4 x GND Notes 1 For distance and range rate when using SN3500 BEING AOT TAGAN Arinc 407 TACAN use appropriate SN3500 DME interface on associated channel TACAN 1 Synchro X OUT Synchro Y OUT Syncro Z OUT TACAN 2 Synchro X OUT Synchro Y OUT Syncro Z OUT S ANDEL Vista Ca itle 7 A SN3500 with TACAN ize Document Number Rev B 82005 10 A reate Friday July 18 2008 Mod Wednesday August 27 2008 Sheet 39 5 4 3 2 1 DATE C
67. N THIS CONFIGURATION THE SN3500 ACTS AS AN INDICATOR FOLLOWING THE RECEIVER SELECTED WITH AN EXTERNAL RELEAY 2 THISIS A GENERIC ILLUSTRATION REFER TO THE SPECIFIC DETAIL DRAWINGS FOR YOUR INSTALLATION 3 THIS INSTALLATION IS THE SAME AS ORIGINAL SN3308 CONFIGURATION S ANDEL Vista Ca e DEVIATION EXT RELAY ES Document Number 82005 1 0 reate Wednesday 18 2005 Mod Sunday December o9 2007 Sheet 3 A B C D E DATE COMMENTS B INITIAL RELEASE INITIAL RELEASE j C A R 806 Minor change corrected pinout for excitation COMPUTER CONTROLLED DRAWING DC CRS HDG DATUM TYPICAL DO NOT REVISE MANUALLY INTERCONNECT SANDEL SN3500 AUTOPILOT SEE NOTE 1 CONCERNING KING KA52 57 HDG DATUM HI HDG DATUM 26 CRS DATUM 40 d CRS DATUM HI SIGNAL GROUND EM CRS HDG DATUM LO Ground 400HZ AC AUTOPILOT TYPICAL INTERCONNECT SANDEL SN3500 AUTOPILOT HDG DATUM 55 HDG DATUM X OR H HDG DATUM Y OR C Note 3 CRS DATUM 40 A CRS DATUM XOR H CRS DATUM Y OR C SIGNAL GROUND Optional 201 ACFT PWR NOTES 1 IF INSTALLATION ALREADY CONTAINS A KING KA52 57 AUTOPILOT 1N4004 ADAPTER IT MAY REMAIN IN THE SYSTEM TREAT THE SN3500 AS A 25 BACK COURSE 2 SN3500 DATUM OUTPUTS ARE REFERENCED TO SIGNAL GROUND Note 4 Aer n 3 CHECK AUTOPILOT INTERNAL SCHEMATIC TO INSURE THAT THE SN3500 IS 0 gt DRIVING THE SIGNAL INPUTS AND THAT IT IS PERMISSABLE TO
68. NAV Converter L L L 1 5 1 4 6 Navigation External NAV Converter L L nnne tentent ees 1 5 1 4 7 Marker BEACON etit u u LES u wak n e T 1 6 1 4 8 Bearing Pointers VOR ADF and 0022444 12 00400 0 ener tenete naa 1 6 1 4 9 ARING Ghanhels 255 2 5 x adco aa uma T IR ned demie etie 1 7 DME INternacia enaa exti de et DINE On An hua as 1 7 1 4 11 Special Considerations for GARMIN GNS430 530 Series sse 1 7 1 4 12 Special Considerations for UPS GXXX U senserat nete n 1 8 1 4 19 Brightness Como arci o dote d D etas Maan teras 1 8 EAA qan bau did dente Ee ICE terete 1 8 1 415 Data Link Weather us endete eaten etie dedi e nasi h aka rade 1 8 SIMPLICI CL DEDE 1 9 1 4 17 Night Vision Support 1 10 1 4 18 Reversionary Attitude 1 10 1 5 y l u ananas aguas 1 10 2 Technical Information 22 2 1 2 1 Deneme a 2 1 2 2 Numbers ice a M E EDI D TEE D TEILE 2 1 2 2 1 Installation
69. NSTALLATION MANUALS FOR COMPLETE WIRING INTERFACE e 2 SN3500 CAN ONLY BE USED AS A SECONDARY DISPLAY S ANDEL Vista Ca 3 TRAFFIC INTERFACE REQUIRES SN3500 SOFTWARE 2 01 OR HIGHER AND PURCHASE OF KEY CODE SN3500 INSTALLATION DRAWING TCAS Il S _ 82005 10 reate Friday March 22 2002 Mod Sunday December 09 2007 Sheet 35 GNS480 GPS RECEIVER PREC APPR SUSPEND IN ILS ENG G S FLAG G S FLAG G S UP G S DN NAV FLAG NAV FLAG CDI LEFT CDI RIGHT TO OBS OUT OBS COS OBS RTN OBS SIN COMPOSITE GND RS232 TXD2 SERIAL GND 429 2 IN A 429 2 IN B GPS INDICATOR 1N4005 SN3500 EHSI ILS1 ENERGIZE GPS OBS HOLD GS Flag GS Flag GS Up GS Down Nav Flag Nav Flag Nav Left Nav Right TO OBS RESOLVER H IN OBS RESOLVER COS OUT OBS RESOLVER E VREF IN OBS RESOLVER SIN OUT NAV 1 COMPOSITE SIGNAL GND RS232 1 RX RS232 1 GROUND 429 OUT A 429 OUT B GPS 1 RELAY SENSE 6 9 98 NOTES A E DATE REV COMMENT C A R 806 INITIAL RELEASE S 1 A R 824 CORRECTED PIN NUMBERING SN3500 LEFT AND RIGHT DEV INPUT COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY 1 GNS 480 SERIAL PORT SETUP ITEMS SERIAL SETUP RX TX SERIAL PORT 2 XXX MAPCOM 9600 ARINC 429 SETUP CH2 IN AHRS LOW 2 SN3500 SETUP ITEMS GPS SELECT IIMORROW GX RS 232 ENH ANNUN SERIA
70. NTURY INSTALLATION MANUAL FOR DETAILS 5 ANY COMMERCIAL 75MW OR GREATER AUDIO TRANSFORMERS MAY BE USED MAGNA TEK TY 141P OR EQUIVALENT ANDEL Vista Ca CENTURY 1C388 COUPLERS Al Document Number 82005 10 reate Monday May 04 1998 Mod Sunday December 09 2007 Sheet 8 A B C D E DATE COMMENTS A INITIAL RELEASE A R 780 MINOR DOC CHANGES COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY S TEC AUTOPILOTS SN3500 S TEC 20 30 T C R C P2 P1 DC HDG HI DC HDG LO S TEC GPSS HEADING SYSTEM S SN3500 S TEC 40 50 PROG COMP S TEC 20 30 40 50 P2 P1 SN3500 33429 CONVERTER 31 DC HDG HI DC HDG SIG HDG CRS RETURN SIGNAL GROUND 29 DC HDG LO 46 SIGNAL GROUND SN3500 T S TEC 55 S TEC 55 60 65 60 2 P1 SN3500 1429 CONVERTER DC HDG DATUM A 28 HDG DATUM HI p so j A Ee rnc P2 20 1 p CI de DC CRS DATUM 40 DC CRS SIG SIGNAL GND 7 U 29 CRS HDG SIGNAL GND 1 7 U HDG CRS 44 SIGNAL GROUND RETURN GROUND SN3500 S TEC 60 65 60 2 RFGC DC HDG DATUM A DC HDG SIG 1 DC CRS DATUM mi Iu DC CRS SIG NOTES 1 SELECT 525 FOR HS EMULATION ON THE FCS MAINTENANCE PAGE SIGNAL GND 9 Y BETUN SANDEL Vista Ca GROUND 97 SN3500 INSTALLATION DRAWING 5 AUTOPILOTS L STECAUTOPLOTS Tuesday September 19 2000 Mod Sunday December 09 2007 Sheet 9 SANDEL SN3500 FLUXGATE X FLUXG
71. NVIS control monitor Page 11 10 Added NVIS ground test step Page 12 2 Added 82005 10 pp 40 updated revisions 82005 IM K Sandel SN3500 Installation Manual Page vi Revision Date 6 16 08 Comments Updated for software version 3 04 and TACAN support Page 1 1 Added export control notice Page 1 2 TACAN added Page 1 6 TACAN added to bearing pointer inputs Page 1 8 NVIS Display Brightness M button LED operation note added Page 1 8 TACAN added Page 2 1 Low voltage operation support note added Page 2 1 Update part number definition Page 2 2 USB cable added to Bill of Materials Page 2 5 Low voltage operation note added Page 2 6 TACAN added Page 2 9 TACAN added Page 2 15 TACAN label added Page 3 4 TACAN added to pinout description Page 3 7 TACAN added to pinout description Page 7 1 Index page updated for TACAN capability Page 7 20 Page updated for NVIS brightness M button LED status Page 11 5 TACAN added to NAV source selection Page 11 6 TACAN added to bearing source selection Page 11 15 TACAN added to enroute operations checks Page 11 16 TACAN approach operations added D1 01 31 08 11 15 07 A R 958 Updated Effective drawing list Modified 82005 10 sheet 28 Added 82005 10 sheet 38 A R 924 Page 1 1 Updated applicable TSOs and ETSO Page 2 1 Lamp kit added Page 2 2 Updated applicable TSOs and ETSO Pages 3 9 amp 3 10 Clarify pin description P2 28 P2 13
72. OMMENTS 27 AUG 08 INITIAL RELEASE AR 1032 Sears COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SN3500 USING INSTRUMENT GROUND NVIS Control Switch See note 2 SN3500 USING REMOTE GROUND NVIS Control Switch gi See note 2 NVIS CONTROL 13 AIRCRAFT GND 11 See note 3 Notes 1 Use 24 AWG stranded shielded 1 or 2 conductor wire as required 2 TYCO P N TT13A9T1 404 toggle switch or equivalent A push on push off pushbutton switch may be used Annunciator not required 3 Use closest available airframe ground 4 In the event of a broken wire fault the SN3500 will default to daylight non NVIS mode S ANDEL Vista Ca itle 7 NVIS CONTROL 07777 0200 10 A reate Wednesday August 27 2008 Mod Wednesday September 10 2008 Sheet 40 1 DATE COMMENTS 02 MAR 09 INITIAL RELEASE AR1055 27 MAY 10 REVISED NOTE 8 AND ADDED CALLOUT TO NOTE 8 ADDED P3 13 REV ATT CONTROL AR1110 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SN3500 USING INSTRUMENT GROUND Reversionary Control Switch See note 2 SG102 AHRS or equivalent device SG102 shown See note 8 Notes 1 Use 24 AWG stranded shielded 1 or 2 conductor wire as required 429 A OUT 2 TYCO P N TT13A9T 1 404 toggle switch or equivalent A 429 B OUT push on push off pushbutton switch may be used Annunciator not required 3 Placard the switch REV 4
73. OT SEE NOTE2 SN3500 SEE NOTE 3 10k HDG SIG 2 2 HDG DATUM HI AC HDG DATUM 1 BOELGOM t HDG DATUM LO 10k CRS SIG 2 C CRS DATUM HI AC CRS DATUM T ROLL COM D CRS DATUM LO 10K 10K NOTES 1 SELECT PN101 FOR HSI EMULATION ON THE FCS MAINTENANCE PAGE 2 SELECT IN831 FOR HSI EMULATION ON THE FCS MAINTENANCE PAGE 3 ANY COMMERCIAL 75MW OR GREATER AUDIO TRANSFORMERS MAY BE USED SUCH AS MAGNA TEK TY 141P OR EQUIVALENT HDG CRS DATUM EXITATION SIGNAL GND EXITATION 26VAC 400Hz FROM 1 INVERTER or AUTOPILOT EXITATION 400 Hz to 5 KHz SANDEL Vista Ca 96113500 INSTALLATION DRAWING BENDIX AUTOPILOTS Document Number 82005 10 reate Tuesday September 19 2000 Mod Sunday December 09 2007 Sheet 5 E DATE COMMENTS _ A_ INITIAL RELEASE A R 780 MINOR DOC CHANGES HONEYWELL qur emm 2 50 PIN COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY HDG DATUM HI CRS HDG KFC 300 DATUM SN3500 KCP 320 LO P2 J HDG VALID AC HDG DATUM 0 HDG DATUM H HDG DATUM C AC CRS DATUM CRS DATUM H KFC 150 SN3500 pura 90 KC191 KC192 CRS DATUM C P BACK COURSE 3 DC HDG DATUM X DC HDG SIG BACK COURSE DC CRS DATUM W DC CRS SIG SIGNAL GND 20 HDG DATUM LO 19 CRS DATUM LO BACK COURSE KFC 200 SN3500 KC 295 220 10 DC CRS DATUM p i W DC CRS SIG 2 SIGNAL GND V HDG CRS INVERTER ri M SIGNAL GND 26VAC 400Hz FROM 1 INVERTER DA
74. Only used when COMP is selected for the NAV signal input A VOR test set should be used to accurately calibrate the displayed bearing pointer reading ENRGZ NONE Selects ILS Energize input 429 429H ACTIVE H ACTIVE L 82005 IM K Sandel SN3500 Installation Manual Page 7 9 Appendix A Post Installation Procedures LOC DV NONE Selects localizer signal input The 429 SN3500 has a built in NAV converter to 429H decode localizer validity and deviation ANALOG from a composite signal input COMP If COMP is selected see following Composite LOC Calibration procedure GAIN Used to calibrate LOC DV COMP GS DV NONE Selects glideslope signal input 429 429H ANALOG OBS CAL DEFAULT 0 0 Calibrates NAV1 OBS DME NONE Selects DME signal input 429 429 MC 568 KSD ANALOG HOLD NONE Selects DME HOLD discrete input to ON HIGH active high or low ON LOW ZERO DEFAULT 000 Present only if Analog DME is selected Use to set zero point of DME input if necessary SCALE DEFAULT 1 00 Present only if Analog DME is selected Use to calibrate DME if necessary 7 1 5 1 OBS Calibration Does not apply to 429 or 400HZ Differential Resolvers Note Maintenance mode and operational mode can be toggled by pressing and holding the CRS knob a In operational mode set the SN3500 course pointer OBS to zero degrees Set the NAV test set to zero degrees b In Maintenance Mode adjust the OBS CAL setting to center the
75. P1 37 VOR LOC FLAG P1 23 VOR LOC FLAG Used when an external NAV converter or analog output GPS is used Differential Low level NAV Flag inputs Superflags are supported with a series resistor see the installation drawings Flag out of view requires greater than 215 mvac on FLAG with respect to FLAG input 24 AWG twisted shielded pair wire is recommended for these functions P1 8 VOR LOC RIGHT Deviation Input P1 38 VOR LOC LEFT Deviation Input Used when an external NAV converter or analog output GPS is used Analog lateral deviation from the VHF navigation receiver or long range navigation receiver LEFT and RIGHT deviation outputs Two dot deflection is 150 mvac 24 AWG twisted shielded pair wire is recommended for these functions P1 24 VOR TO Pointer Input P1 9 VOR FROM Pointer Input Used when an external NAV converter or analog output GPS is used Differential input supports VHF NAV or long range navigation TO pointer and FROM pointer outputs In view is greater than 40 mvac to and 40mvac from 24 AWG twisted shielded pair wire is recommended functions 82005 IM K Sandel SN3500 Installation Manual Page 3 5 Installation P1 39 DME 2 CLK 429B P1 25 DME 2 Data 429A P1 10 DME 2 Sync ARINC 568 Sync or King Clk Data Sync DME REQ signal input NOTE This is DME 2 P1 26 External Brightness Control Broken Wire Detection 0 to 0 5VDC revert to internal control Full Dim 1 5VDC Full Bright 14V Aircraft
76. Page 11 8 11 1 14 11 1 15 11 1 16 82005 IM K Appendix E Checkout Procedures Flight Control System Interface If the SN3500 is interfaced to a flight control system FCS Place the FCS mode selector in heading HDG mode Verify that the aircraft controls respond correctly as the heading knob is turned and the heading bug moves around the SN3500 display Completed Comment Place the FCS mode selector in nav coupled NAV mode Verify that the aircraft controls respond correctly as the course select knob is turned and the course pointer moves around the SN3500 display Completed Comment Switch sequentially through all the NAV sources and verify that the autopilot L R and U D if applicable signals responds correctly to the selected receiver Completed Comment Stormscope Interface If the SN3500 is interfaced to a WX 500 remote lightning sensor Enable the Stormscope display by within the WX menu Verify that WX is annunciated on the SN3500 display Completed Comment Press M and then WX and select WX TEST Verify that the word TEST is annunciated on the SN3500 display for approximately 10 seconds and is then replaced by WX Completed Comment Traffic Sandel SN3500 Installation Manual Page 11 9 11 1 17 11 1 18 11 1 19 Appendix E Checkout Procedures If the SN3500 is interfaced to a traffic processor Activate the TEST function on the traffic processor and verify that
77. RCE 8 ONLY USED WHEN SN3500 IS IN MASTER MODE SELECT GPS1 FOR SENSE ON OBS RELAY CDI MAINTENANCE PAGE SANDEL vista 513500 INSTALLATION DRAWING NAV 1 ARINC 429 GPS INT RELAY ER Document Number 82005 1 0 Rev reate Tuesday April 28 1998 Mod Sunday December 09 2007 Sheet 23 A B C D DATE HHV COMMENTS DATE REV COMMENTS INITIAL RELEASE A R 780 MINOR DOC CHANGES e ADDED NAV2 SENSE OTHER MINOR CHANGES COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY NAV 2 VHF NAV 2 NOTE SN3500 COMP NAV OUT COMP NAV 2 IN ILS ENERGIZE NAV 2 ILS ENERG TO NAV2 RELAY COL Grea NAV2 RELAY OUT FROM NAV2 RELAY GND CLOSURE NAV2 RELAY SENSE GPS 2 GND RS232 2 GROUND RS232 TX RS232 2 RX NOTES 1 FOR 3V COMPOSITE NAV SOURCES INSERT A 470K SERIES RESISTOR LOCATED AT THE SN3500 CONNECTOR NOT REQUIRED FOR 5V SOURCE 2 ILS ENERGIZE AND RELAY SWITCHING OUTPUT ARE ONLY REQUIRED IF NAV 2 IS TO BE USED AS A SECOND PRIMARY VHF NAV RECEIVER IN THIS CONFIGURATION A 2ND SWITCHING RELAY IS ADDED TO SWITCH THE DBAR AND FLAG INPUTS FROM THE 2ND RECEIVER IN THE SAME MANNER AS THE GPS SWITCHING RELAY SHOWN FOR NAV 1 ON THE PREVIOUS PAGE ANDEL Vista Ca itle NAV 2 GPS 2 RS232 Document Number Rev 82005 10 reate Sunday May 03 1998 Mod Sunday December 09 2007 Sheet 24 COMMON NAV CONVERTER INTERCONNECTS
78. S NOT ALLOW FOR AN ADDITIONAL INVERTER DRIVING THE SN3500 2 THIS CONFIGURATION DISABLES THE 328A 3G SLAVING ACTION SLAVING IS PERFORMED INSIDE THE SN3500 4 THIS CONFIGURATION ALLOWS THE USE OF A COLLINS 952 24 WITHOUT USING THE SLAVING FUNCTION OF THE 328A 3G SLAVING ACCESSORY 6 YOU MUST REMOVE THE 323A 3G FLUX COMPENSATOR LOCATED ON TOP OF THE FLUX VALVE GYRO EXT HI GYRO EXT LO RETURN 115 VAC 28 VDC IN FROM BUS 28 VDC IN GROUND 332E4 GYRO EXT LO E D EXT HI NOTE 5 2200 1 4 w or larger F 26VAC ERECT 115V SPIN MTR SANDEL Vista Ca 3 A pan SN3500 INSTALLATION DRAWING NEAN A pe SIGNAL GND 1 EE C ZOUT COLLINS PN101 UPGRADE V Document Number 82005 1 0 reate Tuesday April 28 1998 Sheet 16 SANDEL SN3500 FLUXGATE X FLUXGATE Y FLUXGATE Z FLUXGATE EXCITATION STEPPER STEPPER C GYRO VALID GROUND PER MFG S INSTALL MANUAL AVIONICS E 6 BUS 5 6 N RON HUMPHREY FLUXVALVE NOTE 1 Fluxgate X Fluxgate Y Fluxgate Z Exc H Exc C 4305 150 FV DRIVE GND FV DRIVE ENCODER A ENCODER B GYRO VALID POWER GND 26 VAC OUTPUT 26 VAC GROUND 28 VDC 14 VDC E DATE COMMENTS _ A _INITIAL RELEASE __ a A R 780 MINOR DOC CHANGES B NON GYRO ITEMS REMOVED COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLTY NOTES 1 SELECT STEC 6446 FOR FLUXGATE TYPE AN DE
79. S430 W 530 W 430 530 P4006 P5006 429 OUTA 429 OUT B NAV 1 429 INA NAV 1 429 INB 24 24 429 OUT A VLOC 429 OUT B GPS 1 429 INA GPS 1 429 IN B GPS 429 OUT A GPS 429 OUT B Connection to One Port ONLY 48 49 OR 50 51 GPS 429 In A 1 2 GPS 429 In B 1 2 ILS GPS APPROACH GARMIN 2 GNS430 W 530 W GNS GNS 430 530 P4006 P5006 24 24 RB A VLOC 429 OUT A V VLOC 429 OUT B NAV 2 429 INA NAV 2 429 INB GPS 2 429 INA GPS 2 429 IN B GPS 429 OUT A GPS 429 OUT B Connection to One Port ONLY 48 49 OR 50 51 GPS 429 In A 1 2 GPS 429 In B 1 2 TO AUTOPILOT 1N005 or equivalent FCS ILS ENERGIZE SEE NOTE 4 ILS GPS APPROAC NAV2 RELAY SENSE NAV2 RELAY DISCRETE SPECIAL NOTE SN3500 SUPPORTS GPS VNAV VIA ARINC 429 INTERFACE The connections and components shown in the dashed oval are for historical reference These connections are no longer necessary to support GPS vertical navigation when the SN3500 software has been updated to version 3 02 or later If desired these connections may be retained after converting to GPS VNAV over ARINC 429 1N004 or equivalent TO28VDO 0 2 E DATE COMMENTS INITIAL RELEASE A1 A R780 MINOR DOC CHANGES B RELAY REMOVED PIN NUMBERS INSERTED 26 JAN c ADDED CONNECTIONS FOR GNS ILS GPS APPROACH 09 07 D RELAY SENSE CONNECTIONS amp SETTINGS 12 DEC 07 01 ADDED SPECIAL NOTE N
80. SANDEL SN3500 Primary Navigation Display e fe a AA CER i BRG MEN Installation Manual Sandel Avionics Inc 2401 Dogwood Way Vista CA 92081 Phone 760 727 4900 FAX 760 727 4899 Website www sandel com Email support sandel com 82005 IM K This page intentionally left blank 82005 IM K Sandel SN3500 Installation Manual Page ii Table of Contents 1 Generalilnformation ea ccc 1 1 1 1 MAROC CUI OND LLL 1 1 1 1 1 EXPORT CONTROL NOTICE Lun esses aiaa terne nsn 1 1 1 2 Equipment Description IL ete chy cust etra scere Da tiet anm 1 1 1 2 1 CUP cL 1 1 13 Installation Planning U u u uuu 1 2 1 3 1 Installation Planning Gycl e uu u upa nex feet e rea n eee 1 2 1 3 2 Post Installation S mmani ien aere ef ani ree dee dt ave exe een 1 3 14 lt Interface Plannirig erri n ridet i i u Qasa weaves ii mii i auras 1 3 1 4 1 Compass SySIeITI uet eere d Pea nte he e prd tte o n enr ede a i e 1 3 1 4 2 Autopilot SWItchihgi t Dae Herde dena were e ad enean oe die cepe rat 14 1 4 3 Autopilot Course and Heading Datum esses ete L L L naa 1 5 1 4 4 GPS Annunclalofs imet aere Pre ro D nee B eti e eerie o ya dre 1 5 1 4 5 VLOC Navigation Internal
81. SN3500 including interconnect diagrams mounting dimensions and information pertaining to installation Close adherence to these suggestions will assure optimum performance Unpacking and Inspecting Equipment Exercise extreme care when unpacking the equipment Make a visual inspection of the unit for evidence of damage incurred during shipment If a claim for damage is to be made save the shipping container to substantiate the claim The claim should be promptly filed with the carrier It would be advisable to retain the container and packaging material after all equipment has been removed in the event that equipment storage or reshipment should become necessary 3 2 Installation Considerations 3 2 1 3 2 2 3 2 3 General Considerations The SN3500 should be installed in accordance with standards established by the customer s installing agency and existing conditions as to unit location and type of installation However the following considerations should be heeded before installing the SN3500 Close adherence to these considerations will assure a more satisfactory performance from the equipment The installing agency will supply and fabricate all external cables The required connectors and associated hardware are supplied by Sandel Avionics Cooling Considerations The SN3500 Navigation Display contains its own ventilation fan for internal component cooling and therefore does not require a forced air cooling system Any questions co
82. TAL DME S 5 SANDEL SN3500 ANALOG DME ANALOG DME SANDEL SN3500 SELECTION IF THE DME IS NOT ASSIGNABLE LEAVE THE CORRESPONDING PIN UNCONNECTED SET DME TO LO FR DME1 ON NAV ILS DME 2 MAINTENANCE PAGE TO ENABLE NAV2 DME DISPLAY PAT POTA AOMWMICE ia 1 DME ANALOG 2 IN A DUAL DME CONFIGURATION THE SN3500 CAN ONLY DETECT DME DME REQ DME REQ SIGNAL COM 2 36 DME ANALOG KOLD IT ALWAYS ASSOCIATES DME 1 WITH NAV 1 AND DME 2 WITH DME1 CLK CLK 3 THE SN3500 WILL SUPPORT REMOTE DISPLAY OF KN62 64 DME S CONNECT AS SHOWN TAKING DME REQ FROM REAR CONNECTOR PIN N 6 DME ANALOG VALID THE KN62 64 DO NOT HAVE A HOLD OUTPUT THEREFORE NO HOLD DME ANNUNCIATION IS POSSIBLE HOLD DME1 HOLD P2 DME1 HOLD DATA DATA DME REQ DME REQ DME2 CLK CLK DME HOLD DME1 HOLD SANDEL Vista Ca DME KING SERIAL AND ANALOG Document Number 82005 10 reate Sunday May 03 1998 Mod Sunday December 09 2007 Sheet 31 B D E DATE COMMENTS INITIAL RELEASE TAL AR 780 MINOR DOC CHANGES COMPUTER CONTROLLED DRAWING SINGLE ARINC 568 DME COLLINS DME 40 PE eee nese SHOWN FOR REFERENCE DME 40 SANDEL SN3500 DATA SYNC CLK DME1 HOLD DME1 HOLD RELAY DME NAV 2 DUAL ARINC 568 DME S COLLINS DME 40 3 SHOWN FOR REFERENCE DME 40 SANDEL SN3500 DME1 HOLD DME1 HOLD NOTES 1 INA SINGLE DME CONFIGURATION THE SN3500 DETECTS BOTH DME HOLD AND NAV 1 NAV 2 ASSIGNMENT FROM
83. TIONALLY SKIPPED A R 824 ADDED NOTE 4 FOR FCS SELECTION COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY UPSAT MX20 11 RS422 RX 26 RS422 RX SERIAL HEADING W UPSAT MX 20 NOTES 1 2 35 WX RS 232 GROUND NOTES 1 WX500 ALLOWS ONLY ONE UNIT TO BE MASTER THE MASTER CONTROLS CELL STRIKE MODE AND REMOTE CLEAR THROUGH THE SERIAL PORT 2 WX 500 HEADING CONFIGURATION IS SET TO SERIAL HEADING RECEIVED FROM SN3500 3 A REMOTE CLEAR SWITCH CONNECTED TO THE WX 500 CAN BE USED TO CLEAR THE CELL STRIKE DISPLAY THIS FUNCTION IS ALSO AVAILABLE ON THE FRONT PANEL OF THE SN3500 VIA SOFTKEYS 4 TO ACTIVATE THE HEADING BOOTSTRAP OUTPUT SET THE FCS SELECTION TO OTHER THAN NONE EVEN WHEN THE 533500 15 NOT INTERFACED TO AN FCS C ANDEL Vista Ca itle WX 500 Document Number Rev 82005 10 C1 reate Tuesday September 19 2000 Mod Sunday December 09 2007 Sheet 33 TCAS 791 SN3500 TCAS TRAFFIC 429 A INPUT TCAS TRAFFIC 429 B INPUT SOFTWARE SELECT 1 GOODRICH TCAS 791 A CAS66 SN3500 TCAS TRAFFIC 429 A INPUT TCAS TRAFFIC 429 B INPUT SOFTWARE SELECT 1 HONEYWELL CAS 66 RYAN TAS SN3500 TCAS TRAFFIC 429 A INPUT TCAS TRAFFIC 429 B INPUT SOFTWARE SELECT 1 RYAN 9900 BX TAS i GOODRICH TCAS 791 A ARINC 429 TX A ARINC 429 TX B ON OFF CONTROL TEST ALT OPER STBY GROUND HONEYWELL CAS66 ARINC 429 TX A ARINC 429 TX B Ryan TAS
84. TIVE H selected from list below ACTIVEL SERIAL OBS CAL DEFAULT 0 0 Automatically configured when GPS is selected from list below May require adjustment if the GPS receiver uses an RS 232 interface and has a resolver connected ARINC 429 429 Not shown when selected GPS does 429H not have ARINC 429 output Sandel SN3500 Installation Manual Page 7 16 82005 IM K Appendix A Post Installation Procedures APR ACTV NONE GPS approach active source select ANNUN IN ACTIVE L ACTIVE H GPS Select from list Select the appropriate model of GPS from the list Press the SET soft key CLR button to program 82005 IM K Sandel SN3500 Installation Manual Page 7 17 Appendix A Post Installation Procedures 7 1 9 Page 9 FCS EMULATION SANDEL 9 FCS EMULATION p VOLT R PINS S Vv of CER SEI The FCS Emulation allows the selection and configuration of the FCS interface Configuration Field Options Comment SIGNAL DG Automatically configured when FCS is AC selected from list below HDG DAT RIGHT Automatically configured when FCS is LEFT selected from list below SCL V D Default settings reset when FCS is selected from list below MIN V Default settings reset when FCS is selected from list below MAX V Default settings reset when FCS is selected from list below REF V Default settings reset when FCS is selected from list below CRS DAT RIGHT Automatically configured when FCS is
85. TUM LO PN101 FCS Emulation selected in setup or AUTOPILOT EXITATION 400 Hz to 5 KHz SN3500 KFC 225 P DC CRS DATUM NOTES 1 SELECT KI525 FOR HS EMULATION ON THE FCS MAINTENANCE PAGE DC HDG DATUM HDG DATUM HI 1 SIGNAL GND CRS HDG SANDEL Vista Ca DATUM LO Category SN3500 INSTALLATION DRAWING bu iiis BENDIX KING AUTOPILOTS Document Number 82005 1 0 reate Wednesday September 20 2000 Mod Sunday December 09 2007 Sheet 6 A B C D E DATE COMMENTS B INITIAL RELEASE L l COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY CENTURY IV INTERCONNECT 5KHZ AC VERSION SN3500 5Khz m HDG DATUM 26 HDG DATUM EXCITATION 0 1 50v EXCITATION IV CRS DATU o crs DATUM 0 1 uF 50v NOTES 1 amp 2 CENTURY IV INTERCONNECT DC VERSION SN3500 P2 HDG DATUM 26 a HDG DATUM CRS DATUM 40 a CRS DATUM NOTES 1 amp 2 NOTES 1 SELECT NSD 360DC ON FCS EMULATION MAINTENANCE PAGE 2 ON FCS EMULATION MAINTENANC PAGE ADJUST HDG GRADIENT AND CRS GRADIENT IF USED TO HIGHEST VALUE THAT DOES NOT OVER SHOOT THE LUBBER LINE DURING HDG MODE AND NAV MODE COURSE CHANGES RESPECTIVELY EXCEPT FOR KI 525 THESE VALUES WILL BE IDENTICAL ANDEL Vista Ca e CENTURY IV AUTOPILOTS Document Number 82005 10 reate Monday May 04 1998 Mod Sunday December 09 2007 Sheet 7 CENTURY 1C 388 amp 1C388 M RADIO COUPLERS
86. VIS mode is annunciated onscreen so an external annunciator is not required The input will always pull up to the de activated state when disconnected 1 4 18 Reversionary Attitude Option The SN3500 supports a Reversionary Attitude Display when interfaced to a Attitude Heading Reference System supplying Roll Pitch Heading and lateral acceleration data via Arinc 429 An optional key code is required to enable this feature See the Reversionary Control interface drawing in this manual for interface wiring requirements This option is not available when the SN4500 is interfaced to an analog DME 1 5 Disclaimer Sandel Avionics does not assume any risk for nor accept any responsibility for the interface descriptions contained within this Installation Manual It is the responsibility of the installer to ensure that such equipment is compatible with the SN3500 as described and to ensure that the installation of the SN3500 is accomplished with such equipment using the specific equipment manufacturer s installation and technical instructions No other representations are expressed herein 82005 IM K Sandel SN3500 Installation Manual Page 1 10 Technical Information 2 Technical Information 2 1 General The SN3500 is enclosed in an ARINC 408 form factor enclosure and is mounted to an instrument panel using a standard ATI clamp A black or grey bezel is provided The SN3500 operates on an input voltage from 22 to 33 Volts DC 11
87. ad 60 4K For Glideslope there may need to be a 1K load somewhere else in the system to meet the receiver load requirements Check installation instructions for the interfaced receiver Outputs are protected against shorts to ground Shorts to power supply may cause damage to components Discrete inputs actively pulled to 27 5v through 30k ohms when selected active low or actively pulled to Ov through 30k ohms when selected active high in the maintenance pages This ensures the input is in the inactive state if an external connection fails If interfacing to discrete signals which do not supply a hard Ov 27 5 volt transition any input network may be used that ensures that the discrete input pin is not within 1 0v from its nominal threshold shown in the table either in the active or inactive state Value is for maximum non sustained input voltage maximum sustained voltage is 10 8vdc 82005 IM K Sandel SN3500 Installation Manual Page 2 14 2 6 ARINC 429 2 6 1 ARINC 419 429 Serial Data Receivers Interfaces Technical Information The ARINC 419 429 serial data bus interface provides an information link between the SN3500 and peripheral avionics equipment The bus conforms to 419 429 specifications for electrical characteristics receiving and transmission interval The SN3500 is capable of receiving the following ARINC 419 429 long range NAV ADF TCAS or DME inputs for processing and display as follows
88. ame Signal Type dependent on maintenance page selection 1 Aircraft Pwr In 22 to 33Vdc Power 9 Aircraft Pwr n Power GPS OBS HOLD Out 2 or Open Drain TACAN Relay Out GPS APPR ARM Out 10 or Open Drain TACAN Relay Out 3 Aircraft Ground NH System Ground 11 Aircraft Ground u System Ground 4 GPS1 Relay In Sense Selected Discrete Valid 12 GPS2 Relay In Sense Discrete Valid 5 NAV2 Relay In Sense Discrete Valid NVIS Ctrl In Active Low 13 or Discrete REV Control Analog DME Valid In 6 or Discrete Valid REV Control 14 FCS BACK Out COURSE Open Drain Out 7 GPS1 Relay Open Drain Out 15 GPS2 Relay Open Drain Out 8 NAV2 Relay Open Drain 7 6 5 4 3 2 1 Oh Q Oh 9 Oi 9 14 13 12 11 10 9 OQ 92 49 O Outside View Mating Connector 82005 IM K Sandel SN3500 Installation Manual Page 2 12 Technical Information 2 5 4 Signal Characteristics Table Signal Type Absolute Max Z Q Power Off ote Discrete Valid Low lt 3 5Vdc 914 pe Lo Signal Type Nom Range Absolute Max Z Q Power Off Note 3 29 ET m O 72 Minimum RS232 5Vdc 70mAdc 500 Minimum Open Drain 1Q or High Impedance over 250mAdc gt 350K current protected 82005 IM K Sandel SN3500 Installation Manual Page 2 13 Technical Information Notes At 28Vdc nominal current is 1 4Adc for lamp equipped units and 1 2Adc for LED equipped units 1 minute after start up Power On Lo
89. ar 23 1311 or as appropriate A system design and analysis was conducted with reference to Advisory Circular 2X 1309 1 or as appropriate J Federal Aviation Regulations 2X 1301 2X 1309 a b and d 23 1311 2 1321 b d 2X 1322 2X 1327 a 2X 1331 2X1351 2X 1357 a d 23 1365 2X 1381 2X 1529 and 2X 1581 or as appropriate were the basis of compliance K Installation approval is sought with reference to Flight Standards Information Bulletin FSAW 95 09 Amended titled Electronic Horizontal Situation Indicator EHSI Approvals L The aircraft equipment list and weight and balance were revised and recorded within the aircraft maintenance records M All pertinent records of this alteration are on file at State your repair station name and number 82005 IM K Sandel SN3500 Installation Manual Page 9 2 Appendix D Sample Airplane Flight Manual Supplement 10 Appendix D Sample Airplane Flight Manual Supplement 82005 IM K The following is being provided for installations in which the local FSDO requires an Airplane Flight Manual Supplement This Sample is simply being provided for the convenience of the installer Note that the cover page table of contents and log of revisions has not been included here and will be specific to your installation The text is specific to the installed equipment and also specifies ILS LOCKOUT operation This text must be modified by the installation
90. ass maintenance page Stepper connections are used exclusively for connections to the Bendix King KG 102 or Mid Continent series Directional Gyro when selected in the Compass maintenance page For slaved operation see fluxgate descriptions 24 AWG twisted shielded pair wire is recommended for this connection Hdg Valid Input Connect to the DG valid output if available Not used for 429 sources Selection of the logic level of this pin is in the Compass maintenance page ADF 1 AC X or DC SIN Input TACAN 2 429 419 A ADF 1 AC Y or DC COS Input TACAN 2 429419 B Sandel SN3500 Installation Manual Page 3 4 Installation Inputs from ADF 1 Receiver Selection of AC DC operation is on the ADF maintenance page For DC use P1 20 as the DC reference input For AC inputs Z is grounded 24 AWG twisted shielded pair wire is recommended for these functions P1 20 ADF 1 DC Ref Used when DC SIN COS inputs are used P1 5 Valid Discrete ADF Valid input used if available P1 35 WX500 Ground P1 21 WX500 RS232 Connection to WX 500 Stormscope Use 24AWG twisted pair P1 6 Glideslope FLAG P1 36 Glideslope FLAG Low level GS receiver flag inputs Superflags can be supported with a series resistor see the installation drawings P1 7 Glideslope Deviation Input P1 22 Glideslope DOWN Deviation Input GS deviation input Two dot deflection is 150 mvac 24 AWG twisted shielded pair wire is recommended for these functions
91. atures The Sandel SN3500 Primary Navigation Display is an advanced microprocessor controlled airborne multipurpose electronic display which is FAA approved under technical standard order TSO C6d C34e C35d C36e C40c C41d C113 C118 and C119b The SN3500 is also EASA approved under ETSO C113 The SN3500 employs a patented active matrix liquid crystal AMLCD projection display It is designed to combine the functions of Basic Horizontal Situation Indicator HSI Long Range Navigation GPS or FMS Map Display WX 500 Stormscope Display DME Readout Marker Beacon Indicator NAV Converter Autopilot Switching GPS Annunciators and External Mode Switches Traffic Display FIS B Data Link weather display software version 3 00 and above Optional Class B Night Vision NVIS Compatible Software 3 04 and above Optional Reversionary Attitude Display Software 4 00 and above 82005 IM K Sandel SN3500 Installation Manual Page 1 1 General Information Outputs of heading and course datum and bootstrap heading output are provided as well as L R and U D deviation output and flags The versatile digital and analog interface properties of the unit provide for compatibility with most VHF navigation receivers ADF s TACAN s DME s GPS s remote gyros and flux gates The SN3500 is designed to display the flight plan data from a connected GPS receiver The moving map database for the SN3500 as well as the internal operating system software a
92. be taken SECTION IV NORMAL PROCEDURES The SN3500 NAV pushbutton selects the primary navigation source NAV1 NAV2 or GPS1 The selected source will drive the SN3500 deviation indicator and the autopilot ILS override will prevent selection of the GPS as long as an ILS frequency is tuned on NAV1 or NAV2 This will be annunciated on the SN3500 Navigation Display The SN3500 BRG pushbutton selects the bearing pointer 1 2 both The M pushbutton followed by the BRG pushbutton selects the bearing pointer sources NAV1 NAV2 GPS1 GPS2 or ADF Annunciation of all GPS modes is accomplished by messages on the GPS receiver as well as on screen annunciation on the SN3500 Add following text if Traffic is installed The traffic display mode is annunciated next to the TFC button There are three different modes available which control how the traffic targets are displayed Press the TFC button repeatedly to cycle through the different modes ON Enables display of all targets within the selected map range limited by the maximum range of the installed traffic system M Manual mode Traffic will be displayed at the selected map range only when alerting traffic is present without auto ranging Display range can be changed manually Sandel SN3500 Installation Manual Page 10 2 82005 IM K Appendix D Sample Airplane Flight Manual Supplement A Auto mode Traffic will be displayed at the selected map range only when alerting traff
93. ce page selection 41 IM Marker In 27 MM Marker In 12 OM Marker In 42 429 Out A ree aa for a 28 429 Out B 22 for 13 RS232TxD ee 43 DET pio 29 MSG poze iy ARM pt Out 30 Audio LL Out Audio LL Low Level Audio output requires external amplifier future provision not currently supported 15 OBS LEG te Note 1 volt composite inputs require the use of a series resistor See installation drawings Note 2 For XYZ inputs Z is signal ground P1 1 OQ Q OQ O 0 Qr G y Qr O 44 43 42 41 40 39 38 37 36 35 34 33 32 31 O O 0 O 0 O O O O O Outside View Mating Connector 82005 IM K Sandel SN3500 Installation Manual Page 2 8 2 5 2 Connector P2 Technical Information Pin Name Signal Type dependent on maintenance page selection 16 inverter Exe In Note May be same or different than P1 16 inverter source m Inverter 26Vac Excitation for items on connector P2 1 Shield Gnd In A429 A side 429 EMS TA RS422 side 422 RS232 Ground side In A429 B side 429 1 EMS IB RS422 side 422 RS232 Rx In 2 FMS 2A A429 A side 429 RS232 Ground Side In 32 FMS 2B A429 B side 429 RS232 Rx 18 ILS Energize1 In Discrete In Discrete Valid Discrete Open Gnd or Open 28Vdc In A429 A side 429 3 NAVIA A407 Synchro X Z grounded A710 Composite Video In 33 NAV1B A429 B side 429 A40
94. cter key code to enable traffic Use the BRG and MEM keys to select the character and the MAP and TFC keys to move the cursor TCAS Model Collins TCAS 4000 Select the appropriate model of 2 TCAS from the list Press the SET IC Honeywell CAS 66 2 ese button to program Honeywell CAS 67 Users of Honeywell KTA 810 Honeywell CAS 81 systems should configure as CAS Ryan 9900BX TAS 66 Sandel SN3500 Installation Manual Page 7 23 82005 IM K Appendix A Post Installation Procedures 7 1 13 Page 13 STATUS SANDEL 13 STATUS VALUE SRC gt CER arri a Sensor summary status 82005 IM K Sandel SN3500 Installation Manual Page 7 24 7 1 14 Page 14 BRT DATA BLK SAND eI N3500 14 BRT DATA BLK 82536954 lt mz U H F w X CtR BRGJ MEM Configuration Field Options Selection P1 26 BRIGHTNESS CONTROL DATA RECORD BLK INTERNAL EXTERNAL NONE Selects the brightness control to be Appendix A Post Installation Procedures Comment external or internal Monitors external brightness bus voltage Not shown when brightness control selection is set to INTERNAL Min Brt V Norm Adjusts the external brightness bus to the desired night brightness voltage Adjustable from 1 5 volts to 15 0 volts Not shown when brightness control selection is set to INTERNAL Min Brt V NVIS Adjusts the external brightness bus to the desired NVIS brightness voltage Adjustable f
95. d In the event the aircraft has an existing GPS switch annunciator panel or it is desired that one be installed the GPS SELECTED input on the SN3500 is used to remote 82005 IM K Sandel SN3500 Installation Manual Page 1 4 1 4 3 1 4 4 1 4 5 1 4 6 General Information sense the selection of the GPS1 and annunciate the selection This is referred to as slave mode It allows annunciation of the selection on the SN3500 but does not use the front panel NAV switch to select the GPS receiver This mode is only available for use with a single GPS Master Slave mode selection is done in the NAV maintenance page When any relay is used the SN3500 uses a wraparound RELAY SENSE input which provides feedback of failure of the switching relay A pole on the external relay is used to ground an SN3500 input pin when the relay is in the energized position If the low signal is not detected the SN3500 annunciates the relay failure by redlining the NAV source display Autopilot Course and Heading Datum Course and heading datum outputs are provided These can be selected to be AC or DC in the Flight Control System FCS maintenance page and depending on whether Datum Excitation is connected The direction sense of these signals can be reversed as required A Back course discrete output is provided for annunciation or AFCS reverse course control when required This operates during LOC operation when the aircraft is flying with the tail
96. deviation needle C Set the test set to 45 degrees Turn the course pointer to re center the deviation needle If it is with a few degrees of 45 degrees then proceed Otherwise if it is about 90 degrees out change the OBS ROT setting on Maintenance Page 10 to REVERSED and return to step a d Check the to from flag on the SN3500 display If to from is reversed and correct wiring has been verified adjust the OBS CAL 180 degrees from the current setting 82005 IM K Sandel SN3500 Installation Manual Page 7 10 Appendix A Post Installation Procedures e Check the course pointer at 30 degree increments and verify calibration 7 1 5 2 Composite LOC Calibration Procedure The following procedure applies to SN3500 installations that have been configured to use the SN3500 internal localizer converter LOC DV COMP This procedure does not apply for any other LOC DV setting such as Arinc 429 or Analog from an external LOC converter Ramp or Bench Test Perform the following procedure using the respective aircraft receiver This test may be performed with a ramp test set or may be performed on the bench with a signal generator at nominal RF signal level 25uV or greater 1 On the SN3500 NAV maintenance page select LOC DV and change to COMP to select Composite Localizer Select GAIN Set 0 DDM STD on the test set and tune the receiver to match the LOC frequency on the test set Adjust the SN4500 GAIN value so
97. e the remote directional gyro Verify that the compass card is displayed in amber AND that a warning message is displayed on the SN3500 which requires operator acknowledgement Completed Comment NAV Source Selection If the SN3500 is configured in master mode no external NAV GPS switch Press the NAV button repeatedly and verify that the screen legend next to the button cycles correctly through the configured NAV sources i e NAV1 NAV2 GPS1 GPS 2 TACAN 1 TACAN 2 or as configured For each NAV source create valid and invalid NAV conditions and verify correct display of the SN3500 NAV flag for each receiver the large red X through the CDI For each VOR LOC source verify that tuning an ILS frequency causes the glideslope vertical deviation scale to display on the screen even if it is flagged Completed Comment If ILS Lockout is enabled Press the NAV button and select a source other than NAV1 such as GPS or NAV2 if configured Tune NAV1 to an ILS frequency and verify that after a one second delay the selected NAV source automatically reverts to NAV1 Verify that as long as NAV1 is tuned to an ILS frequency pressing the NAV button will not change the NAV source but instead will display the message NAV1 TUNED TO LOC Verify that upon de tuning the ILS frequency from NAV1 the NAV source selection returns to its original state Completed Comment If NAV2 is configured tune both NAV1 and NAV2 to an ILS
98. e Flight control system operation Completed Comment Additional Testing Perform any additional flight testing deemed necessary Completed Comment Sandel SN3500 Installation Manual Page 11 18 Appendix F List of Effective Drawings and Attachments 12 Appendix F List of Effective Drawings and Attachments Drawing Rev Title 82005 07 A LAYOUT SN3500 82005 05 A Layout SN3500 INSTALLATION 82005 10 pp 1 D POWER AND INVERTER 82005 10 pp 2 FCS DEVIATION INT RELAY 82005 10 pp 3 C FCS DEVIATION EXT RELAY 82005 10 pp 4 C FCS GENERIC CRS HDG DATUM 82005 10 pp 5 C BENDIX AUTOPILOTS 82005 10 pp 6 C BENDIX KING AUTOPILOTS 82005 10 pp 7 B CENTURY IV AUTOPILOTS 82005 10 pp 8 A1 CENTURY 1C388 COUPLERS 82005 10 pp 9 A1 S TEC AUTOPILOTS 82005 10 pp 10 B KING KG102A SN3500 SLAVING 82005 10 pp 11 B KCS55 BOOTSTRAP XYZ 82005 10 pp 12 B S TEC AERONETICS GYRO 82005 10 pp 13 B XYZ GYRO GYRO SELF SLAVED 82005 10 pp 14 B XYZ GYRO 82005 10 pp 15 C XYZ GYRO WITH KMT112 82005 10 pp 16 C COLLINS PN101 UPGRADE 82005 10 pp 17 B MID CONTINENT 4305 82005 10 pp 18 C SN3500 COMPASS BOOTSTRAP 82005 10 pp 19 A1 KCS 55 REMOVAL REF 82005 10 pp 20 C NAV 1RS 232 GPS EXT RELAY 82005 10 pp 21 C NAV 1 RS 232 GPS INT RELAY 82005 10 pp 22 C2 NAV 1 ARINC 429 GPS EXT RELAY 82005 10 pp 23 C NAV 1 ARINC 42
99. e purpose of simplifying ground tests of the SN3500 A copy of this report and the Operational Flight Check Procedures Report must be retained by the installing agency and a copy must be installed in the aircraft maintenance records A copy must also be forwarded to Sandel Avionics Inc along with the Warranty Registration Form Part Number 10235 which should be mailed after operational acceptance Repair Station Name Number Address or Location ST ZIP A C Model Technician Date Performed 82005 IM K Sandel SN3500 Installation Manual Page 11 1 Appendix E Checkout Procedures COMPANY NAME COMPANY ADDRESS TELEPHONE FAX Ground Test Procedures Report For Sandel Avionics SN3500 Installed in aircraft make and model Registration No SN3500 Serial No Document No Rev Date 82005 IM K Sandel SN3500 Installation Manual Page 11 2 11 1 1 11 1 2 11 1 3 11 1 4 82005 IM K Appendix E Checkout Procedures Introduction The following ground test procedures are to be performed after the SN3500 has been properly configured in the Post Installation Procedures but prior to performing flight test procedures Successful completion of both the Ground Test and Flight Test procedures is necessary to support the claim that the SN3500 as installed performs its intended function and is compatible with all aircraft systems The ground test procedures contained herein will include testing of interface
100. ed In addition bearing pointer 1 will have AUTO listed as a choice Completed Comment Select each available NAV source for each pointer and verify in turn that the depicted bearing corresponds to the actual bearing shown on the NAV source Completed Comment DME Selection If two DME receivers are installed and configured Verify that pushing NAV to select between NAV1 and NAV2 also switches the appropriate DME readout on the SN3500 distance display Press M and then BRG to configure bearing pointer 1 to be NAV1 and bearing pointer 2 to be NAV2 Press BRG to display both pointers simultaneously Verify that the correct DME data is displayed in each bearing pointer data block Sandel SN3500 Installation Manual Page 11 6 Appendix E Checkout Procedures Completed Comment If a single DME receiver is installed and is not switchable between NAV1 and NAV2 Verify that pushing NAV to select between NAV1 and NAV2 causes the DME readout to be displayed when NAV1 is selected and the DME readout to be removed when NAV2 is selected Press M and then press BRG to configure bearing pointer 1 to be NAV1 and bearing pointer 2 to be NAV2 Press BRG to display both pointers simultaneously Verify that DME data is displayed in the bearing pointer 1 data block and that no distance data is displayed in the bearing pointer 2 data block Completed Comment If a single DME receiver is installed and is switchable between NAV1 and NAV2 Veri
101. eet 26 itle A B C D E DATE COMMENTS A INITIAL RELEASE 22 A R 780 MINOR DOC CHANGES B PINS CHANGED NOTES UPDATED C 806 MINOR DOC CHANGE COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY GNS GNS SN3500 430 530 GARMIN P4006 P5006 Nav 429 In A Port 1 2 VLOC 429 Out A Nav 429 In B Port 1 2 VLOC 429 Out B Connection to Desired Pins for unit 1 or 2 429 Out A Connection One 429 Out B ort 48 49 OR 50 51 3 GPS 429 In A Port 1 2 GPS 429 In B Port 1 2 MAIN PORT ANALOG THIS 6 WIRE INTERCONNECT PERFORMS THE FOLLOWING TO AUTOPILOT OR SEE SANDEL FCS GPS VLOC AUTOPILOT SWITCHING DEVIATION INT RELAY DIAGRAM IF ADDITIONAL RECEIVERS ARE SWITCHED TO RSE RESOLVER pn MESO THE AUTOPILOT E DEVIATION 1 AUXILIARY MECHANICAL RESOLVER MAY BE USED ON THE 430 TO FROM MAIN PORT 2 FLAGS INAVIOR2 GNS430 ARINC ANNUNCIATORS NAV 1 OR 2 ARINC 429 MODE SWITCHING 4 GARMIN SETUP ITEMS SOFTWARE MAIN 2 07 OR LATER MAIN ARINC 429 CONFIGURATION IN 1 LOW SANDEL EHSI OUT LOW GAMA 429 Graphics w Int SDI LNAV 1 SDI1 VOR LOC GS ARINC 429 CONFIGURATION SPDRX LOW SPDTX LOW SDI VOR ILS 1 SDI1 ANDEL Vista Ca SINGLE SN3500 GNS430 530 82005 10 reate Thursday January 07 1999 Mod Sunday December 09 2007 Sheet 27 A SANDEL SN3500 GARMIN 1 GNS GNS GN
102. es and pin out corrections 82005 IM K Sandel SN3500 Installation Manual Page vii Revision Date Comments A1 04 21 2005 A R 780 minor doc and dwg changes A 03 31 2005 Initial release 82005 IM K Sandel SN3500 Installation Manual Page viii General Information 1 General Information 1 1 1 1 1 1 2 1 2 1 Introduction The information contained within this Installation Manual describes the features functions technical characteristics components approval procedures installation considerations setup procedures checkout procedures and instructions for continued airworthiness for the Sandel Avionics SN3500 Primary Navigation Display The SN3500 is the industry s most capable electronic HSI It can be used to directly replace a mechanical DG or HSI as a primary display or the SN3500 can be used as a replacement or upgrade for an existing Sandel SN3308 navigation display It is signal but not plug compatible with the SN3308 and is an upgrade in performance with both an improved display and added features EXPORT CONTROL NOTICE The TACAN display option software key p n 90143 TCN is subject to the licensing jurisdiction of the Department of State in accordance with the International Traffic in Arms Regulations ITAR 22 CFR 120 130 It may not be exported sent transferred disclosed or otherwise released to a foreign person without a license issued by DDTC Equipment Description Fe
103. facility to be compatible with the installed equipment SECTION GENERAL The Sandel Avionics SN3500 Primary Navigation Display PND is a compact three inch instrument that performs the functions of a traditional Horizontal Situation Indicator combined with a two pointer RMI The SN3500 also displays a moving map Stormscope data FIS B data link weather traffic information marker beacon and GPS annunciators if the aircraft is appropriately equipped and configured Add following text if Data Link Weather is installed FIS B Weather Data is intended for the purpose of assisting in long range strategic flight planning only Please note that its delayed updating and lack of sufficient resolution makes it unsuitable for tactical maneuvering of the aircraft It also differs significantly from on board weather radar which scans a narrow vertical angle since it portrays radar returns from multiple ground stations extending from the surface up to the highest flight levels For these reasons it may not even directly reflect the current flight conditions SECTION LIMITATIONS The system must utilize software version X XX or later FAA approved version The SN3500 Navigation Display Pilots Guide SPN 82005 PG or applicable revision corresponding to the software version must be immediately available to the flight crew The CRC Self Test Failed message must not appear on power up if flight operations are predicated on the use of the SN35
104. frequency and verify that NAV1 remains selected Detune the ILS frequency on NAV1 and verify that the display reverts to NAV2 Completed Comment If the SN3500 is configured in slave mode using external NAV GPS switch Verify that pressing NAV does not change the selected NAV source but instead displays an advisory message Completed Comment Sandel SN3500 Installation Manual Page 11 5 11 1 9 11 1 10 11 1 11 82005 IM K Appendix E Checkout Procedures Verify that the external NAV GPS switch arrangement correctly controls the selected NAV source on the SN3500 including any ILS lockout scheme if implemented Completed Comment LOC GS Deviation Using a ILS test signal generator verify proper deviation of the LOC GS deviation indicators on the SN3500 Tune the NAV1 to match the ILS test signal generator frequency usually 108 1 MHz Select LOC 1 on the SN3500 Adjust the signal generator to verify the following indications on the SN3500 LOC deviation indicator center 2 dots fly left 2 dots fly right and LOC flagged Adjust the signal generator to verify the following indications on the SN3500 GS deviation indicator center 2 dots fly up 2 dots fly down and GS flagged Repeat for NAV2 Completed Comment BRG Source Selection Press M and then press BRG on the SN3500 and verify that all installed NAV sources are presented for each bearing pointer NAV1 NAV2 ADF1 ADF2 TACAN 1 TACAN 2 GPS1 GPS2 as install
105. fy that pushing NAV to select between NAV1 and NAV2 causes either the correct DME readout to be displayed or a none indication depending on the position of the external DME select switch if installed Press M and then press BRG to configure bearing pointer 1 to be NAV1 and bearing pointer 2 to be NAV2 Press BRG to display both pointers simultaneously Verify that DME data is displayed in the bearing pointer 1 data block when DME is externally switched to NAV1 Verify that when DME is externally switched to NAV2 an arrow gt appears in the DME portion of the pointer 1 data block and that DME distance data is displayed in the bearing pointer 2 data block Press BRG to deselect pointer 1 and only display pointer 2 Verify that proper DME data is now displayed in the bearing pointer 2 data block Completed Comment If an external DME HOLD control is configured Verify that enabling DME HOLD displays the H symbol for each installed DME receiver so equipped Completed Comment 11 1 12 GPS Interface and Control For each GPS receiver installed and configured 82005 IM K Sandel SN3500 Installation Manual Page 11 7 11 1 13 82005 IM K Appendix E Checkout Procedures Allow the receiver to acquire a valid position fix and press NAV on the SN3500 to select that receiver as a NAV source Enter either a single destination waypoint or a flight plan on the GPS receiver and select normal LEG navigation mode Verify that
106. he Sandel Avionics Model SN3500 Navigation Display The assumption made is that all functions of the SN3500 will be used in an essential primary navigation function Replace the SN3500 backlight lamp when necessary utilizing instructions in the SN3500 Component Maintenance Manual document number 82005 0133 82005 IM K Sandel SN3500 Installation Manual Page 6 1 Appendix A Post Installation Procedures 7 Appendix A Post Installation Procedures After all wiring has been verified and the SN3500 has been installed into the panel the maintenance pages must be accessed to properly configure the SN3500 for the installed equipment Prior to applying power to the SN3500 depress and hold the BRG and the MEM keys and then apply power to the unit Continue to hold until the first maintenance menu appears This protocol insures than maintenance menus cannot be called up accidentally during flight Once the Maintenance Menu is entered press the NEXT or LAST softkeys to cycle the MAINTENANCE MENU pages Use the UP DOWN arrow keys for selections and rotate the right knob to adjust and select On some menus additional soft key legends will appear as prompts Escape the maintenance menus by pressing and holding the CRS knob This will allow normal operation of the unit to test the effects of settings Re enter the maintenance pages pressing and holding the CRS knob To disable maintenance menu operation power down and restart normally
107. ic is present except that the map range will auto scale to an appropriate range to show the traffic on screen Manual M or Auto A modes do not display non alerting traffic Add following text if Data Link Weather is installed The SN3500 can display two types of weather information precipitation and lightning Lightning may be displayed from two independent sources WX 500 Stormscope or a FIS B data link receiver Both sources of lightning may be displayed simultaneously The SN3500 WX pushbutton selects the type weather to be displayed PL Precipitation amp Lightning s Precipitation only i5 Lightning only The M pushbutton followed by the WX pushbutton selects the lightning display data source either WX500 WSI or both The number to the right of the WX annunciation displays the time in minutes since the last FIS B precipitation data was received from the data link receiver Weather graphics depicted on the SN3500 data link weather display may differ significantly from the on board weather radar or from out of the cockpit observations for one or more of the following reasons Vertical strata information is not provided by the FIS B weather service The FIS B weather data originates from NEXRAD ground based weather radar observations that include weather measurements up to 30 000 feet above the radar facility The on board weather radar is measuring returns relative to the current flight level The FIS B weather dis
108. inter and adjust the CRS V D setting as appropriate c Use the REF V adjustment to center the heading and course rollout if not precisely on the lubber line This will rarely be required HDG DAT and CRS DAT allow the direction sensing to be reversed during installation Changing these settings is identical to reversing H C on a synchro control transformer The other settings on this page are not for installer adjustment except on advice of the factory service bulletin or service information letter Note that the adjustments are shown in the left column of values The right column shows the default values for reference purposes 82005 IM K Sandel SN3500 Installation Manual Page 7 19 7 1 10 Page 10 OBS RELAY CDI NN 10 OBS RELAY CDI P VOLT R PINS L V s CtR a BRG MEM Appendix A Post Installation Procedures Configuration Field Options Comment OBS ROT NORMAL Adjusts rotation of OBS REVERSED Select DIFF A when interfaced to DIFF A 400HZ differential resolver BTSTRP NONE Enables bootstrap synchro heading NORMAL output REVERSE MODE MASTER Selects NAV GPS switching mode SLAVE In MASTER mode the SN3500 s NAV button is used to switch between NAV and GPS sources In SLAVE mode a remote switch is used SENSE NONE Enables relay sense input to verify GPS1 relay switching If a low is not GPS2 detected on the relay sense input the GPS1 GPS2 corresponding NAV source
109. ion Manual Page iv 1 1 46 Page 16 Software GRO iuc said an eet deaf eet eed po beta Ro 7 28 8 Appendix B Environmental Qualification Form 8 1 9 Appendix C Sample FAA Form 337 24 242 9 1 10 Appendix D Sample Airplane Flight Manual Supplement 10 1 11 Appendix E Checkout Procedures u 11 1 11 1 Functional Ground Test Procedures Report U ener neret tnnt nnne 11 1 Tip CIntrodictioniis noir neci i eet n ML ir d ce Me bar A nii e m c odd 11 3 11 1 2 Test Procedures Results 5 etse eite tectae Peek 11 3 T1113 Physical Installation ioc MA e i e cr e et ie dei eie ac 11 3 11 1 4 Wiring Verification and Initial Power Up U L 11 3 11 1 5 System Configuration J ate a wide tet elata te th reda ia ana 11 4 11 1 6 System FUNCTIONS a eet re edd te ei Po e REDE 11 4 1421277 Compass System Interface eee ede kasa rear p ite edidic 11 4 11 1 8 NAV Source Selection aeter tr etd oe en aed 11 5 EOO GS D6VIatloh ete atid De n lod fe 11 6 11 1 10 Source Selection Leste a t eee eR Sta 11 6 11 1 11 DME Selectlon
110. isfactory brightness level can be attained Completed Comment Evaluate the display of the SN3500 for readability Completed Comment Evaluate the intensity properties of the SN3500 display under both direct and indirect sunlight conditions and in nighttime operation conditions Completed Comment 82005 IM K Sandel SN3500 Installation Manual Page 11 15 11 5 2 82005 IM K Appendix E Checkout Procedures Check the function of all buttons and knobs and confirm that all controls are operational Completed Comment Enroute Operations Cycle various aircraft electrical equipment such as lights landing gear radar windscreen heat and anti icing boots Verify that none causes interference on the SN3500 display Completed Comment Verify proper operation of one or both VHF NAV receivers as installed both as NAV sources and as bearing pointer sources Simultaneously verify proper channeling and display of one or both DME sources as installed Completed Comment Verify proper operation of one or both long range NAV receivers as installed both as NAV sources and as bearing pointer sources Include verification of map display of waypoints Completed Comment Verify proper operation of one or both TACAN receivers as installed both as NAV sources and as bearing pointer sources Completed Comment Verify proper operation of one or both ADF sources as bearing pointers if installed Completed Comment Sandel SN350
111. ished to verify proper wiring See FUNCTIONAL GROUND TEST PROCEDURES REPORT in the appendix for verification of this step and other checks F The Functional Pinout Descriptions on the following pages will assist you in determining installation requirements Adhere to all notes within these descriptions and on installation wiring diagrams G Special caution must be taken to observe 30 Hz OBS resolver connections in order to prevent possible damage to the installed VOR localizer converter 82005 IM K Sandel SN3500 Installation Manual Page 3 2 82005 IM K Installation See Installation Wiring Diagrams and the MAINTENANCE MENU Configuration Instructions for notes pertaining to these considerations Ground Bonding In order to assure installation characteristics match the DO 160 RF and Lightning test conditions ensure that two ground wires of at least the recommended size are installed in accordance with the installation drawings and these wires are connected to a bonded aircraft ground Ensure that shielded wiring is used to the Flux Gate if installed Gyro Reference and Gyro XYZ if installed Power Wiring To assure that the SN3500 will operate properly down to its rated minimum input voltage of 22Vdc ensure that two power wires of at least the recommended size are connected from the SN3500 circuit breaker to the SN3500 in accordance with the installation drawings Sandel SN3500 Installation Manual Page 3 3 3 3 Signal In
112. lag output derived from selected NAV source referenced to Ground Connect corresponding input to P2 1 Gnd P2 28 FCS Lateral Deviation Output Right LL lateral deviation from selected NAV source Connect corresponding deviation input to P2 1 Gnd P2 13 FCS Vertical Deviation Output UP LL vertical deviation from selected NAV source Connect corresponding deviation input to P2 1 Gnd P2 43 FCS Lateral Superflag Output Superflag output derived from selected NAV source P2 29 FCS Vertical Superflag Output Superflag output derived from selected NAV source P2 14 RS 232 TX Output2 RS 232 serial FIS B data link output Software Rev 3 0 and above P2 30 ARINC2 429 A Output P2 15 ARINC2 429 B Output Low or high speed ARINC 429 output which transmits selected course and selected heading for ARINC 429 Long Range NAV receivers 24 AWG twisted shielded pair wire is required for these functions Connector P 3 Pinout Descriptions P3 1 amp P3 9 Display Primary Power Input 22 33Vdc Connection to both pins is required using two 20AWG wires and a 5 ampere circuit breaker Maximum power required is 35 watts Connection to the avionics bus is recommended to reduce voltage fluctuations during engine start P3 3 amp P3 11 Display Power Return Input Pins 3 and 11 are the aircraft ground input connections Connection to both pins is required using two 20 AWG wires Either pin should also be used for the digital
113. ncerning cooling can be verified in the post installation checkout by monitoring the SN3500 Internal temperature on the System maintenance page Mechanical Installation Considerations The SN3500 installation should conform to customer requirements and airworthiness standards affecting the location and type of installation 25 1321 a stipulates that Each flight navigation and power plant instrument for use by any pilot must be plainly visible to him from his station with the minimum practicable deviation from his normal position and line of vision when he is looking forward along the flight path 82005 IM K Sandel SN3500 Installation Manual Page 3 1 3 2 4 Installation 25 1321 b stipulates The flight instruments required by 25 1303 must be grouped on the instrument panel and centered as nearly as practicable about the vertical plane of the pilot s forward vision In addition 25 1321 b 4 states The instrument that most effectively indicates direction of flight must be adjacent to and directly below the instrument in the top center position Similar regulations apply to FAR Part 29 Transport Category Rotorcraft and to Part 23 Small Airplanes Refer to Sandel Avionics Drawing No 82005 titled Layout SN3500 Installation for specific assembly and mounting instructions Electrical Installation Considerations Connections and functions of the SN3500 are described in this section Refer to the SN
114. ndel SN3500 Installation Manual Page 7 4 Appendix A Post Installation Procedures CAL N 25 0 25 0 Calibration settings for fluxgate input CAL E See below CAL W CAL S 7 1 3 1 Compass Calibration Applies to installations using a fluxgate input When a flux gate is first selected the quadrant and peaking adjustments will be automatically set The magnetic heading shown in the value field at the top of the page should be within 20 of the aircraft s wet compass reading The magnetic heading reading should also increase and decrease as appropriate when the aircraft is turned If this is not the case the following troubleshooting procedure can be used to diagnose fluxgate problems a Align the aircraft to north Set the CAL settings to 0 0 Adjust the quadrant setting until the magnetic heading is 20 of north If it is not possible to come within 20 of north then the XYZ connections the fluxgate may actually be YZX or ZXY Take all three wires off the fluxgate and move them one terminal clockwise and retest as above It may be necessary to repeat this step Once the magnetic heading reads within 20 of north then the correct Z leg has been identified and should not be changed Note When installing to existing wiring ensure that the fluxgate center tap that exists on some Honeywell Sperry and Collins fluxgates is not connected b Ensure that the compass card rotation is correct by
115. ng Induced Tra nsient Susc eptibility 22 0 XX EF 2 PASS Lightning Direct Effects 23 0 x Icing 24 0 x Electrostatic Discharqe 25 0 A PASS 82005 IM K Sandel SN3500 Installation Manual Page 8 1 Appendix B Environmental Qualification Form RTCA DO 160E Environmental Qualification Form LED Models NAMEPLATE NOMENCLATURE A2F 17 BBB H R R BBI G IXXXXXXZBABBC W W M XXE2F2X XX AX TYPE MODEL NO 543500 TSO NUMBERS C113 C5e C d C34e C35d C36e C40c C41 d C52b C118 MANUFACTURER S SPECIFICATION AND OR OTHER APPLICABLE SPECIFICATION MANUFACTURER Sandel amp vionics Inc ADDRESS Vista CA 22081 REVISION amp CHANGE NOS OF 00 150 Revision E DATE TESTED ENVIRONMENTAL RTCA DO Equipment TESTS DO 160E Test SECTION Category x ATI AT emnperciture 5252 45 8452 Ground Survival Operctional High Termpercture 453 amp 454 Ground Survival Operational In Flight Loss of Cooling 455 PASS Altitude 461 PASS Decompression 462 Credit per Sandel Doc No 82007 0144 Overpressure 463 PASS Venen 5131589 Humicity O Operaferer SHOCK are Ces m8 RESONANT FREQUENCIES Section 7 2 Step a and d Pre 5can X V Hz Y 50Hz I 190Hz PostScan X 180Hz Y 295Hz I 190Hz Section 8 13 Steps a and e Pre 5can X 180Hz Y 50Hz I 17 PostScan X 17 Hz Y 274Hz 1 150Hz Section 8 13 Steps b and d Pre 5can X 180Hz Y
116. nstallation drawings for details 24 AWG twisted shielded triple conductor is recommended for these signals HDG CRS Datum Excitation This is a ground referenced 400 5Khz excitation input for the HDG Datum and CRS Datum outputs only This input is only used if referenced on the applicable installation drawing If unused Connect P2 10 to 28vdc P3 1 Course Datum Output Heading Datum Output These function are either AC or DC Course Datum and Heading Datum for the flight control system If AC signals the excitation reference is P2 10 Selection of AC DC gain and direction of rotation are accomplished on the FCS maintenance page 24 AWG single conductor shielded wire is recommended for each of these functions HDG Bootstrap X out HDG Bootstrap Y out Z Ground NOTE Referenced to P1 16 This function may be used to provide bootstrap output to an RMI or other directional instrument in the form of ARINC 407 synchro 24 AWG twisted shielded pair wire is recommended for these functions Drive only electronic loads with this output limited to 60ma max FCS ILS Energize Out Active low open drain output to FCS when selected navigation source vertical deviation is enabled FCS Lateral Flag Output Low Level flag output derived from selected NAV source referenced to Ground Connect corresponding input to P2 1 Gnd Sandel SN3500 Installation Manual Page 3 9 3 3 3 Installation P2 42 FCS Vertical Flag Output Low Level f
117. o the aircraft 5 Assemble required tools Recommended crimp tools are given in the following table 82005 IM K Sandel SN3500 Installation Manual Page 1 2 1 3 2 General Information Recommended Crimp Tools High Density Standard Density 22 28 AWG 20 24 AWG Eres Sasi Positioner Esa asnan Tool Positioner Tool Military P N M22520 2 01 M22520 2 09 M81969 1 04 M22520 2 08 M81969 1 02 Positronic 9507 9502 3 M81969 1 04 9502 5 M81969 1 02 ITT Cannon 995 0001 584 995 0001 739 N A 995 0001 604 980 2000 426 AMP 601966 1 601966 6 91067 1 601966 5 91067 2 Daniels AFM8 K42 M24308 18 1 K13 1 M24308 1 02 Astro 615717 615725 M81969 1 02 615724 M81969 1 02 Post Installation Summary 1 2 3 4 5 Prior to power up review correct wiring by using standard ohmmeter and voltage checks Insure the correct orientation and positioning of the three SN3500 D connectors The connector numbers are printed on the back of the SN3500 for reference Review special items such as connection of the NAV receiver resolver wiring Apply power to the SN3500 bring up in maintenance mode and sequentially access each SN3500 maintenance page to correctly select the installed equipment Perform Ground Test procedures Perform Flight Test procedures 1 4 Interface Planning 1 4 1 Compass System Determine whether the SN3500 is to be used internally slaved or unslaved Unslaved o
118. observing that the magnetic heading reading increases decreases properly as the aircraft is turned Reverse the XY inputs from the fluxgate to correct for reverse rotation if necessary Compass calibration is completed by aligning the aircraft at each cardinal heading and adjusting the corresponding calibration value until the magnetic heading reading observed on the compass maintenance page matches the actual aircraft heading After the four cardinal points have been adjusted and verified a final check of the systems should be done by power cycling the SN3500 into normal mode and ensuring the compass rose is correct for each cardinal heading NOTE Changes to the compass calibration settings may take up to two minutes to take effect when observing the compass card in normal operational mode Therefore It is recommended to make these calibration adjustments on the compass maintenance page where the compass readings are instantaneous and not affected by the slaving logic in the SN3500 82005 IM K Sandel SN3500 Installation Manual Page 7 5 Appendix A Post Installation Procedures Reversionary Attitude Configuration ARINC 429 Low High speed only When the HEADING source is configured as ARINC 429 an optional Reversionary Attitude Mode is available for activation via a valid key entry Once configured and valid The assigned input discrete connected to an external switch controls the switching between his Mode and Reversionary Attitude Mode
119. of approximately 4 5vdc WARNING You must check the NAV receiver wiring before installation planning and before applying power to the system to prevent NAV receiver damage from inadvertent miswiring Refer to the Sandel installation drawing This resolver will operate from 30Hz to 500Hz and is calibrated in the NAV maintenance page b An electronic 400Hz differential resolver is provided for use with 400Hz receivers such as Collins VIR 30A This interconnect uses SIN COS inputs Z ground referenced and SIN COS outputs Z ground referenced Marker Beacon Three inputs are provided for a Marker Beacon repeater These are DC level sensitive inputs The thresholds and logic levels are adjusted by selection of the appropriate equipment type on the MKR maintenance page Lamp load resistors are internal The SN3500 can also monitor label 222 when marker beacon data is provided from an ARINC 429 source Bearing Pointers VOR ADF and TACAN 82005 IM K Sandel SN3500 Installation Manual Page 1 6 1 4 9 General Information The bearing pointers can derive their information from any of the connected navigation receivers including two composite NAV inputs ADF s TACAN s and the long range navigation receivers through the serial ports ADF s can be connected as ARINC 407 synchro or DC SIN COS inputs See the installation drawings for interconnection data and select the appropriate format from the ADF maintenance page The composi
120. of receivers based on the selection in the LNAV maintenance page 82005 IM K Sandel SN3500 Installation Manual Page 3 6 Installation P1 30 Audio Out LL audio output to the audio panel for optional callouts alerts Future use not currently supported 3 3 2 Connector P 2 Pinout Descriptions P2 1 Signal Ground Return Input This common Signal Ground Return is used for P2 analog signal grounds such as the Z lead of synchros and analog signal shield grounds See the installation wiring diagrams for details Do not use this pin to connect digital signal ground return shields or use this for power ground return P2 16 AC Excitation Input for P2 inputs Connection to this pin is required only if functions of ARINC 407 synchro or 400Hz AC sine and cosine inputs on P2 It does NOT apply to outputs on P2 The input requirements are 26Vac nominal 400Hz Input frequency is 560 Hz maximum and 240 Hz minimum Input impedance is 220KQ 24 AWG shielded wire is recommended for this function P2 31 GPS1 FMS 1 429A 422 232 Gnd P2 17 GPS1 FMS 1 429B 422 232 Signal Main input from GPS FMS 1 P2 2 GPS2 FMS 2 429A 422 232 Gnd P2 32 GPS2 FMS 2 429B 422 232 Signal Main input from GPS FMS 2 P2 18 VHF 1 ILS Energize Input This pin controls the Vertical Deviation Bar when selected to NAv1 These signals also control the ILS Lockout logic so the SN3500 can sense when a GPS receiver is inappropriately selected as the primary NAV source
121. on Services Broadcast FIS B data link weather precipitation and lightening input via a single RS 232 Input from a WSI Data Link receiver in software version 3 00 and above Purchase of a key code to 82005 IM K Sandel SN3500 Installation Manual Page 1 8 General Information enable the weather display is required See the WSI Data Link Receiver interface drawings in this manual for interface wiring requirements The 5 3500 can be configured to operate as the sole weather display or a listener when another display is installed and configured to command the WSI receiver When the SN3500 is the sole display the WSI receiver RS 232 interface must be configured as NO FLOW CONTROL see the WSI receiver manual for details regarding receiver configuration 1 4 16 TACAN The SN3500 supports TACAN input via ARINC 419 ARINC 429 and Arinc 407 Synchro XYZ A TACAN key code is not required for maintenance page setup however purchase of a key code to enable the TACAN display is required When configured TCN will not appear as a NAV source selection or on the bearing pointer source list if the TACAN key is not valid See the TACAN interface drawings in this manual for interface wiring requirements 82005 IM K Sandel SN3500 Installation Manual Page 1 9 General Information 1 4 17 Night Vision Support Option For NVIS capable units NVIS mode is enabled by a closure to ground through an external toggle switch or maintained pushbutton switch N
122. or required In Differential pair to pin 6 36 GS1 LL Flag in Flag 22 GS1 LL Dev In In Differential pair to pin 7 FLY DOWN Polarity indicates above glideslope fly down indication 7 GS1 LL Dev In In Differential pair to pin 22 FLY UP Polarity indicates below glideslope fly up indication In Differential pair to pin 23 37 LAT1 LL Flag In Flag Note For use with external SUPERFLAG see installation drawing for series resistor required In Differential pair to pin 37 23 LAT1 LL Flag In Flag 8 LAT1 LL Dev In In Differential pair to pin 8 FLY RIGHT Polarity indicates left of course fly right indication 38 LAT1 LL Dev In In Differential pair to pin 38 FLY LEFT Polarity indicates right of course fly left indication In Differential pair to pin 9 24 To From In Flag Note For use with external SUPERFLAG see installation drawing for series resistor required In Differential pair to pin 24 9 To From In Flag In 39 DME 2 CLK A568 In 25 DME 2 DATA A568 In 10 DME 2 SYNC A568 In 40 DME 2 Hold Discrete Valid In n c A429 A side 429 26 oba R422 side 422 R232 Ground side A407 Synchro X In n c A429 B side 429 11 Spare 1 R422 side 422 R232 Rx A407 Synchro Y 82005 IM K Sandel SN3500 Installation Manual Page 2 7 Technical Information P1 Connector continued from previous page Pin Name Signal Type dependent on maintenan
123. otes 1 AUXILIARY MECHANICAL RESOLVER MAY BE USED ON THE 430 MAIN PORT 2 SN3500 MAINTENANCE PAGE ITEMS PAGE 5 NAV ILS DME 1 NAV 429 FR ENRGZ 429 LOC DV 429 GS DV 429 PAGE 6 NAV ILS DME 2 NAV 429 FR ENRGZ 429 LOC DV 429 GS DV 429 PAGE 7 GPS 1 AS APPROPRIATE SELECT GNS 430 ARINC OR GNS500 ARINC ANNUN SERIAL LAT DV SERIAL VERT DV SERIAL VERT ENA SERIAL PAGE 8 GPS 2 AS APPROPRIATE SELECT GNS 430 ARINC OR GNS500 ARINC ANNUN SERIAL LAT DV SERIAL VERT DV SERIAL VERT ENA SERIAL DUAL GNS INSTALL ONLY PAGE 10 OBS RELAY CDI MODE MASTER SENSE NAV2 NS GPS2 NAV2 amp GPS2 3 GARMIN SETUP ITEMS SOFTWARE MAIN 2 07 OR LATER MAIN ARINC 429 CONFIGURATION RECEIVER 1 IN 1 LOW SANDEL EHSI OUT LOW GAMA 429 Graphics w Int SDI LNAV 1 SDI1 VOR LOC GS ARINC 429 CONFIGURATION SPD RX LOW SPD TX LOW SDI VORIILS 1 SDI1 MAIN ARINC 429 CONFIGURATION RECEIVER 2 IN 1 LOW SANDEL EHSI OUT LOW GAMA 429 Graphics w Int SDI LNAV 2 SDI2 VOR LOC GS ARINC 429 CONFIGURATION 2 SPD RX LOW SPD TX LOW SDI VOR ILS 2 SDI2 GNS 430W 530W INSTALLATIONS SET VNAV TO ENABLE APR ACTV TO ANNUN IN 4 RELAY AND CONNECTIONS TO GNS ILS GPS APPROACH ONLY USED WITH 430W OR 530W RELAY ONLY REQUIRED FOR DUAL GNS INSTALLATION SANDEL Vista Ca 220 613500 INSTALLATION DRAWING SINGLE SN3500 DUAL GNS430 W 530 W Document Number 82005 1 0 itle reate Thursday January 07
124. peration would be appropriate when the SN3500 is bootstrapped to an already slaved compass system or is being slaved to a panel mounted DG with bootstrap output Plan for 82005 IM K High Resolution Digital Output from a Mid Continent 4305 series DG with gyro valid output flux gate 10 Vac Fluxgate Excitation and Internal 26Vac Inverter internal slaving Sandel SN3500 Installation Manual Page 1 3 1 4 2 General Information Quadrature stepper motor drive input from a Bendix King KG 102 series DG with compass valid output and flux gate connected directly to SN3500 internal slaving m 3 wire ARINC 407 synchro DG with or without gyro valid output and fluxgate internal slaving m 3 wire ARINC 407 synchro remote or panel mounted DG self slaved with or without gyro valid output SN3500 unslaved m ARINC 429 Heading Input from AHRS Sandel monitors for Label 320 Magnetic Heading Data and Label 270 System Status SN3500 unslaved Internal slaving requires connection of the flux gate excitation to the SN3500 flux gate reference input P2 24 This input is used only to demodulate the flux gate signals DG s with XYZ bootstrap outputs require the master 400Hz inverter to be connected to the SN3500 400Hz reference input on P1 16 This input is used to lock all 400Hz inputs on P1 and 400Hz outputs the SN3500 This input presents no loading to the source Follow the information on the installation drawings and plan to set up
125. play is not exactly real time Under certain circumstances the time from when the NEXRAD radar observations were made to when the data is displayed on the SN3500 can be as high as 40 minutes During this time the position of the weather may have significantly changed or moved relative to the aircraft position The graphic representation of precipitation is predicated on the level of reflected energy from moisture in the air mass the more moisture in the air mass the higher level of energy returned to the radar antenna This may result in graphic presentation of precipitation on the SN3500 display when no visible moisture can be seen Virga precipitation the precipitation may be at a higher flight level and evaporating before reaching the current aircraft flight level Sandel SN3500 Installation Manual Page 10 3 82005 IM K Appendix D Sample Airplane Flight Manual Supplement The circuit breaker for the SN3500 Navigation Display is located on the lower right circuit breaker panel labeled EHSI 1 Refer to the SN3500 Primary Navigation Display Pilots Guide for other procedures error messages alerts and more detailed FIS B data link weather information SECTION V PERFORMANCE DATA No Change to AFM Sandel SN3500 Installation Manual Page 10 4 Appendix E Checkout Procedures 11 Appendix E Checkout Procedures 11 1 Functional Ground Test Procedures Report The Functional Ground Test Procedures Report below is for th
126. re field loadable through the use of a portable computer equipped with a USB port and a USB capable version of Microsoft Windows Although simple retrofit replacement of most existing three inch PNI s or HSPs is possible without additional features we strongly encourage complete installation of the unit with all compatible peripheral equipment interconnected to maximize its functional capability 1 3 Installation Planning Sandel Avionics has taken many equipment interface possibilities into consideration during the design of the SN3500 to ensure maximum interoperability with other avionics Contact the factory with any questions about interfacing to specific avionics equipment not covered in the installation drawings To simplify installation and installation planning signals are wired to the SN3500 pins per the installation diagrams and software setups are used in a post installation procedure to assign protocols gradients to each pin based on the equipment connected There are separate maintenance menu pages for each equipment function and in most cases the selections are made by equipment make model 1 3 1 Installation Planning Cycle 1 Compile an equipment list for the aircraft 2 Study the feature list below and determine the desired functional characteristics for the installation 3 Study the installation drawings to determine a basic interconnect scheme and check for conflicts 4 Develop the specific wiring diagrams unique t
127. rom 1 5 volts to 15 0 volts Not shown when brightness control selection is set to INTERNAL Not applicable to non NVIS units DATA RECORD BLK None For factory use Calibrating the external brightness control minimum brightness BEFORE performing calibration Select the BRT maintenance page select EXTERNAL for brightness control 82005 IM K Sandel SN3500 Installation Manual Page 7 25 Appendix A Post Installation Procedures To calibrate minimum brightness set aircraft to NVIS OFF and do the following from BRT maintenance page Please note The maintenance page always displays at 100 brightness You need to exit MAINT by pressing and holding the left knob to see the resulting brightness adjustment 1 Select Min Brt V Norm with up down arrow keys 2 Set the aircraft external brightness bus at the desired night brightness voltage This voltage will be displayed on screen 3 Press SET softkey This will set Vzero See graph below at the current bus voltage minus 2 00 volts 4 Exit MAINT by pressing and holding the left knob and check the brightness balance with the rest of the cockpit If you need further adjustment re enter BRT maintenance page by pressing and holding the left knob and trim the Min Brt V Norm setting using softkeys A lower voltage setting number will INCREASE the brightness Repeat steps 1 2 3 4 with external NVIS selected NOTE From this point on the pilo
128. s LOC DV NONE Selects localizer signal input The 429 SN3500 has a built in NAV converter to 429H decode localizer validity and deviation ANALOG from a composite signal input COMP If COMP is selected see Composite LOC Calibration procedure in the previous section GAIN Used to calibrate LOC DV COMP GS DV NONE Selects glideslope signal input 429 429H ANALOG OBS CAL DEFAULT 0 0 Calibrates NAV2 OBS See OBS calibration instructions for NAV1 in section 7 1 5 1 DME NONE Selects DME signal input 429 For installations with a single DME 429 MC receiver used by NAV1 and NAV2 568 select LO FR DME1 if low on DME2 KSD Hold P1 40 indicates NAV2 selection LO FR DME1 or HI FR DME1 if high on DME2 Hold HI FR DME1 P1 40 indicates NAV2 selection HOLD NONE Selects DME HOLD discrete input to ON HIGH active high or low Not shown if above ON LOW DME selection is LO FR DME1 or HI FR DME1 82005 IM K Sandel SN3500 Installation Manual Page 7 13 7 1 7 Page 7 GPS1 CER t BRG MEM Appendix A Post Installation Procedures The GPS1 page allows the selection and configuration of the GPS1 input Configuration Field Options Comment ANNUN NONE Automatically configured when GPS is ACTIVEL selected from list below SERIAL LAT DV NONE Automatically configured when GPS is ANALOG selected from list below SERIAL VERT DV NONE Automatically configured when
129. s to other systems Therefore this ground test must be conducted in conjunction with or subsequent to ground testing of other systems The following external system interfaces will be tested Heading input from directional gyro Compass input from fluxgate sensor if installed Navigation data inputs VOR ILS GS ADF DME GPS and FMS if installed Annunciator inputs from a marker beacon receiver if installed Annunciator inputs from a GPS receiver if installed Lightning strike inputs from a WX 500 Stormscope sensor if installed Remote NAV source switching relays and or indicators if installed External NVIS control switch if installed Test Procedures and Results Physical Installation Verify that the SN3500 clamp tray has been properly installed in accordance with the manufacturer s instructions that any external switches affecting SN3500 operation have been clearly labeled and that a trip free resetable circuit breaker labeled is clearly visible Ensure that cooling air intake is not obstructed Completed Comment Wiring Verification and Initial Power Up Perform a 100 continuity check of all aircraft wiring to verify in accordance with installation wiring diagrams Completed Comment Sandel SN3500 Installation Manual Page 11 3 11 1 5 11 1 6 11 1 7 82005 IM K Appendix E Checkout Procedures Power check all wiring to ensure that 28 Vdc and 26 Vac if applicable are applied
130. screte Output Can be used to operate a switching relay whenever GPS1 or Lorant is selected by the NAV pushbutton The receiver type is selected on the LNAV1 maintenance page P3 8 VHF NAV2 Switching Relay Discrete Output Can be used to operate a switching relay whenever VHF NAV2 is selected by the NAV pushbutton VHF NAV2 is enabled on the NAV2 maintenance page P3 10 GPS APPR ARM Discrete Output or TACAN Relay Out Open Drain active low output used to select APPR ARM mode of the external GPS receiver Accessible during normal use from the pilots NAV menu operation Can also be used to operate a switching relay or external annunciator whenever a TACAN is selected by the NAV pushbutton The TACAN receiver s are configured on the NAV maintenance pages P3 12 GPS2 Relay Sense Feedback from GPS2 relay if used P3 13 NVIS Ctrl or REV Control For NVIS capable units NVIS mode is enabled by a closure to ground through an external toggle switch or maintained pushbutton switch NVIS mode is annunciated onscreen so an external annunciator is not required 82005 IM K Sandel SN3500 Installation Manual Page 3 11 Installation For Reversionary Attitude Display units the Reversionary Display is enabled by a closure to ground through an external toggle switch or maintained pushbutton switch The input will always pull up to the de activated state when disconnected P3 14 AFCS Back Course Discrete Output Open Drain Used to feed the back
131. sed when the Garmin GNS430 530 ARINC NAV receiver which uses ARINC 429 only is being used If more than one receiver is used which has analog signaling this will require switching relays to feed the single set of SN3500 inputs Deviation only NAV converters not providing bearing information are supported There are only low level flag inputs If it is desired to use a Superflag instead of a low level flag from the NAV receiver a series resistor must be used to the low level input and the input is grounded See the installation drawings Optional ILS lockout of the GPS selection is provided by an ILS Energize 1 2 input pins This feature can be disabled on the NAV maintenance page In the Master mode this will cause the SN3500 to revert to and annunciate NAV1 when an ILS is tuned on NAV1 NAV2 when an ILS is tuned NAV2 Disabling of ILS lockout is called for when the customer does not want ILS lockout operation or when a GPS receiver with vertical guidance is used to drive the ILS Energize pin during GPS operation In this situation NAV1 GPS1 use ILS Energize 1 and NAV2 GPS 2 use ILS Energize 2 to display vertical guidance For analog receivers two types of resolvers are supported a An electronic OBS resolver with rotor input and SIN COS outputs is provided An associated DC reference pin must be connected to the stator low side connection of the NAV receiver This may be ground but may also be a DC reference voltage
132. signal ground shields return as required The number of shields will vary depending upon the functions wired to Connector P3 P3 2 GPS OBS or HOLD Command Discrete Output or TACAN Relay Out Open Drain active low output used to operate the OBS function of Bendix King KLN 90 GPS receivers or the HOLD function of the Morrow and Garmin GPS receivers Accessible during normal use from the pilots GPS MODE soft key 82005 IM K Sandel SN3500 Installation Manual Page 3 10 Installation Can also be used to operate a switching relay or external annunciator whenever a TACAN is selected by the NAV pushbutton The TACAN receiver s are configured on the NAV maintenance pages P3 4 GPS1 Relay Sense GPS SELECTED Input This input is used when the SN3500 is set up for slave mode so an external GPS switch can be used to switch to an external GPS receiver Causes proper mode switching and annunciation on the SN3500 display This input is active only when enabled in the OBS RELAY CDI maintenance page 10 P3 5 NAV2 Relay Sense Feedback from NAV2 relay if used When replacing a SN3308 with the SN3500 see configuration page 7 14 P3 6 Analog DME Valid or REV Control Discrete input for Analog DME valid or Reversionary Display On OFF control For Reversionary Attitude Display units the Reversionary Display is enabled by a closure to ground through an external toggle switch or maintained pushbutton switch P3 7 GPS1 Switching Relay Di
133. stallation Details The following information is in the same order as the summary pin description list in the prior section 3 3 1 Connector P 1 Pinout Description P1 1 P1 16 P1 31 P1 17 P1 2 P1 32 P1 3 P1 33 P1 19 P1 4 P1 34 82005 IM K Signal Ground Return Input This common Signal Ground Return is used for P1 analog signal grounds such as the Z lead of synchros and analog signal shield grounds See the installation wiring diagrams for details Do not use this pin to connect digital signal ground return shields or use this for power ground return Primary AC Excitation Input for P1 inputs Connection to this pin is required only if functions of ARINC 407 synchro or 400Hz AC sine and cosine inputs are used on P1 NOTE This is also the reference for synchro referenced outputs on the opposite connector P2 The input requirements are 26Vac nominal 400Hz Input frequency is 560 Hz maximum and 240 Hz minimum Input impedance is 220KQ 24 AWG shielded wire is recommended for this function TCAS 429 A TCAS 429 B Optional ARINC 429 input for traffic Data link A Data link B Optional input for FIS B data link Software Rev 3 0 and above Hdg X Hdg 429A DG Stepper A Input Hdg Y Hdg 429B DG Stepper C Input Master HDG inputs For XYZ type directional gyro ground the Z leg to signal ground P1 1 This input is referenced to the 26Vac 400Hz reference on P1 16 This function is selected on the Comp
134. t lt M z 2 4 z 9 3 Composite 1 In me id ADE MODIFIEDNOTE SITO INCLUDE 2 i 18 ILS1 ENERGIZE x COMPUTER CONTROLLED DRAWING 4 APPR ACTIVE be BM x DO NOT REVISE MANUALLY 4 SEE NOTE 2 6 GS Fla 36 GS Flag NAV 1 AND ARINC 429 GPS INTERCONNECT VERT FLAG KLN90 B SHOWN FOR REFERENCE L N VERT UP GS Up 22 VERT DOWN SiS RDOND Nav FI LAT FLAG Nav FI LAT FLAG av Flag NOTES 1 CONNECT OBS H FROM RECEIVER H or C WHICHEVER IS THE ACTIVE OUTPUT CHECK APPROPRIATE NAV RECEIVER SCHEMATICS CONNECT SIN OUT and COS OUT TO THE ACTIVE RETURN PINS USUALLY D F CONNECT OBS VREF TO EITHER Nav Left LAT LEFT 3 Nav Right STATOR RETURN PIN REF OR GROUND USUALLY E or G THE LOAD RESISTOR LAT RIGHT SIMULATES A SYNCHRO TO 2 THE APPROACH ACTIVE OUTPUT FROM THE GPS TO THE AUTOPILOT MAY HAVE TO BE AN ADDITIONAL RELAY SEE THE MANUFACTURERS INSTALLATION DIAGRAMS KLN90 B SHOWN SEE NOTE 5 TO VHF NAV RECEIVER RESOLVER INTERCONNECT FROM 3 THE PREFERRED INSTALLATION IS THE SN3500 P3 7 CONTROLLING AN EXTERNAL SWITCHING RELAY IF AN EXISTING SWITCH CONTROL BOX IS INSTALLED AND IT IS DESIRED TO LEAVE IT OPERATIONAL USE P3 4 TO SENSE GPS MODE AND SELECT SLAVE FOR THE MODE SETTING ON THE OBS RELAY CDI MAINTENANCE PAGE OBS RESOLVER H IN MASTER SDI 1 2 SEE NOTE 9 SN3500 CONTROLS THE NAV GPS
135. t will be able to trim the minimum brightness if desired using the M button to enter the pilot s menu 100 Brightness Extern Brt Bus Volts Vmax aircraft pwr Av Pilot Maintenance Brightness Page Trim Adjustment 82005 IM K Sandel SN3500 Installation Manual Page 7 26 Appendix A Post Installation Procedures 7 1 15 Page 15 Power SANDEL 15 POWER CER 3 BRG MEM Monitors power inputs to the SN3500 including the 1 and 2 inverters 82005 IM K Sandel SN3500 Installation Manual Page 7 27 Appendix A Post Installation Procedures 7 1 16 Page 16 Software CRC SANDEL 16 SFTWR CRC COMPUTED CRC UPDATE CER MEM Displays CRC values for the software and database programs Press the UPDATE soft key to re calculate Contact Sandel if FAIL is annunciated for any of the values 82005 IM K Sandel SN3500 Installation Manual Page 7 28 Appendix B Environmental Qualification Form 8 Appendix B Environmental Qualification Form RTCA D0 160D Environmental Qualification Form Lamp Models NAMEPLATE NOMENCLATURE A2 F1 ZBAB H R XXXXXXZBA BB WW M XXF2 XXA MODEL SN3500 TSO NUMBERS C113 MANUFACTURER S SPEC IHC ATION AND OR OTHER APPLIC ABLE SPECIHC ATION a Design Requirements amp Objectives For SN3500 EHSI doc ument number 82006 0010 b RICA DO 160D Environmental Plan For Sandel SN3500 EHSIdocument number 82006 0090 MANUFACTURER Sandel Avionics
136. te 3 AlliedSignal Electronics and Avionics KX 155 Communications and Navigation Receiver or as appropriate 4 AlliedSignal Electronics and Avionics 10A Radar Altimeter System or as appropriate 5 AlliedSignal Electronics and Avionics KR 22 Marker Receiver or as appropriate 6 AlliedSignal Electronics and Avionics KG 102A Directional Gyro or as appropriate 7 AlliedSignal Electronics and Avionics 112 Magnetic Azimuth Transmitter or as appropriate By example state the following functional interface properties C The SN3500 receives and processes GPS navigation information for digital and waypoint display from the GPS165 These operations are considered supplemental navigation 82005 IM K Sandel SN3500 Installation Manual Page 9 1 Appendix C Sample FAA Form 337 D The SN3500 receives and processes VOR localizer and glideslope deviation and composite audio for bearing display from the KX 165 These operations are considered primary means of navigation E The SN3500 receives and processes glideslope deviation and composite audio for bearing display from the KX 155 F The SN3500 receives and processes marker beacon receiver information for illumination from the KR 22 G The SN3500 receives and processes magnetic heading for digital and graphic display from the KG 102A and KMT 112 H Interference and functional tests and inspections were accomplished with reference to Advisory Circul
137. te NAV inputs accept standard 0 5v ARINC inputs For 3v inputs a series resistor is required please see the appropriate installation drawing Selection of 0 180 phase is made by the appropriate maintenance page calibration ARINC Channels The SN3500 contains universal inputs capable of communicating with ARINC 429 ARINC 419 RS232 and Analog All equipment capable of ARINC compatibility such as GPS FMS Navigation Traffic etc can be directly connected to the appropriate signal input There are a total of 17 compatible ARINC inputs 1 4 10 DME Interface 1 4 11 DME inputs support ARINC 429 ARINC 568 King serial or analog 40mV mile inputs Analog DME is supported only in software versions 2 01 or higher Special Considerations for GARMIN GNS430 530 Series Required SN3500 Setup Items Maintenance Study the Sandel Maintenance Page Items on the appropriate GNS430 Page Items installation drawings and set as indicated Relay Mode MASTER ILS Lockout OFF Required GARMIN GNS430 Setup Items Receiver 1 Software Main 1 00 or later Main ARINC 429 IN 1 Low Sandel SN3500 Configuration OUT Low GAMA 429 Grph w Int Note NOT ARINC 429 SDI LNAV1 SDH VOR LOC GS Speed RX Low ARNG 29 MEME SDI VORIILS 1 SDH Required GARMIN GNS430 Setup Items Receiver 2 82005 IM K Sandel SN3500 Installation Manual Page 1 7 General Information
138. the appropriate compass selections on the compass system maintenance page Internal slaving does not require the use of an external slaving accessory Compass calibration is performed using the SN3500 Compass maintenance page The SN3500 will provide standby heading operation from the flux gate alone in the event of directional gyro DG failure The SN3500 has a 3 wire ARINC 407 synchro bootstrap compass output if required which is capable of driving electronic loads Autopilot Switching The SN3500 has low level deviation and flag outputs intended to drive an autopilot These outputs feed from the pilot selected navigation source These outputs may eliminate the need for an external autopilot switching relay However if an external switching relay is used for instance for compatibility with an existing installation the SN3500 has protected Open Drain relay output discretes intended to drive external switching relays These outputs have 250ma maximum current and pull to within 1 ohm of ground NAV1 selection is the default selection and no relay driver output discrete is available The NAV2 GPS 1 or GPS 2 outputs can be used to operate a switching relay for each source allowing the pilot to control the NAV source selection from the front panel of the SN3500 This is referred to as master mode and it is the preferred mode of installation In this configuration an additional remote switch annunciator panel for a GPS receiver is not require
139. the course pointer automatically rotates to the desired track and that groundspeed and waypoint ID are displayed on the SN3500 Completed Comment Press M and then press BRG and assign either bearing pointer to the selected GPS receiver Verify that the bearing pointer corresponds to the bearing to waypoint and that the distance displayed matches the display on the actual receiver Completed Comment If the GPS is equipped with an OBS mode Bendix King or a HOLD mode which enables course resolver input Garmin select the OBS or HOLD mode and verify that rotating the course select knob turns the course pointer Verify that the needle centers on the correct bearing to waypoint Completed Comment Enter the CDI and Annunciator Test mode of the GPS if available Verify proper response of the GPS annunciators if configured to display on the SN3500 If external mode selection is enabled on the SN3500 verify that the GPS pushbutton softkeys accessed in NAV menu control the proper GPS functions Completed Comment Marker Beacon Interface If a marker beacon receiver is interfaced to the SN3500 With a marker beacon test set generate outer middle and inner marker signals respectively Verify that the appropriate annunciation appears on the SN3500 Completed Comment Press TEST mode on the marker beacon receiver and verify that the MT symbol appears on the SN3500 Completed Comment Sandel SN3500 Installation Manual
140. the test pattern is displayed on the SN3500 Completed Comment NVIS Control If the SN3500 supports NVIS compatibility SN3500 XXXN Activate the external NVIS control switch and verify NVIS is annunciated on the lower right of the screen Completed Comment Reversionary Display Control If the SN3500 is configured to support the Reversionary Attitude Display Activate the external REV control switch and verify the SN3500 displays a representative horizon and compass arc for the attitude of the aircraft Place the REV control switch back in the normal position and verify the SN3500 switches back to the normal HSI display Completed Comment Additional Testing Perform any additional tests deemed necessary Completed Comment 11 2 EMI RFI Test Procedures 11 2 1 82005 IM K Nav Com Testing Sandel SN3500 Installation Manual Page 11 10 Appendix E Checkout Procedures Apply power to the avionics bus and ensure that all electrical equipment including the SN3500 is operating normally Open the squelch on the primary communications radio and tune the radio to each whole megahertz frequency sequentially Attempt to discern any interference caused by the SN3500 Pull the SN3500 breaker if interference is noted to verify that the SN3500 is the source Completed Comment Repeat for the secondary communications radio Completed Comment Tune the primary navigation radio to 112 MHz and enable the audio output A
141. tic Direction Finding ADF equipment TSO C118 Traffic Alert and Collision Avoidance System TCAS Airborne Equipment TCAS TSO C119b Traffic Alert and Collision Avoidance system TCAS Airborne equipment TCAS II Software Certification RTCA DO 178 Level C Environmental Categories RTCA DO 160D E 2 3 3 Technical Standard Order Stipulation The following stipulation as presented is required by the Federal Aviation Administration for articles approved under Technical Standard Order This statement does not preclude multiple installation and operational approvals in regard to specific aircraft make model or type The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standard TSO articles must have separate approval for installation in an aircraft The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements 2 3 4 Installation and Operational Approval Procedures For the purpose of seeking installation approval declarations should be made in the Description of Work Accomplished section of a Federal Aviation Administration FAA Form 337 or other field approval or other limited supplemented type certification form A sample Form 337 is
142. tion Manual Page 11 13 Appendix E Checkout Procedures COMPANY NAME COMPANY ADDRESS TELEPHONE FAX Flight Test Procedures Report for Sandel Avionics SN3500 Installed in aircraft make and model Registration No Serial No Document No Rev Date 82005 IM K Sandel SN3500 Installation Manual Page 11 14 Appendix E Checkout Procedures 11 4 Introduction The Flight Test Procedures described below are to be performed after both the Post Install Procedures and the Ground Test Procedures are performed Successful completion of the Flight Test Procedures will then satisfy the criteria for operational acceptance of the SN3500 installation Specific procedures are not provided for many of the tests herein due to differences in installed options and aircraft configurations Refer to the SN3500 Pilots Guide and the proposed Airplane Flight Manual Supplement for operational details of the equipment Each test item is followed by a space for the initials of the person performing the procedure and a space for a description of any observations or anomalies Determination of a successful flight test is made after analysis of these observations 11 5 Test Procedures 11 5 1 Pre Departure Operations Apply power to the SN3500 and all associated equipment Determine that all equipment initializes and functions normally Verify that the SN3500 internal brightness control can control the brightness of the SN3500 and that a sat
143. tional Ground Test Procedures Report and an Operational Flight Check Procedures Report is also included in the appendix and should be used as a basis for validating the SN3500 equipment configuration and for verifying proper installation and functional performance A copy of this form should be submitted along with the FAA Form 337 or other approval or certification form A permanent copy must be filed and maintained by the installing agency Another copy must be presented to the aircraft owner for entry into the aircraft maintenance records as well as a copy forwarded to Sandel Avionics along with the Warranty Registration Form Part Number 10129 to be filed after completion and installation acceptance If any difficulty is experienced with the functionality or operational performance of the SN3500 contact Sandel Avionics for assistance 82005 IM K Sandel SN3500 Installation Manual Page 2 4 Technical Information 2 4 Physical and Electrical Properties 2 4 1 Physical Dimensions Form Factor ARINC 408 Width 3 175 in 8 04 cm Height 3 175 in 8 04 cm Length 10 17 in 25 83 cm overall flush to bezel 9 82 in 24 94 cm measured from rear of bezel Weight 2 88lbs 1 31 Kg LED models 3 0 lbs 1 36 Kg Lamp models CG 5 1 from rear of bezel ATI Clamp Sandel Avionics P N 61062 Cooling Requirements Internal fan requiring ambient air at fan input 2 4 2 Summary Operational Characteristics Tempera
144. to 33 volts DC on units with serial number 5 2500 or higher nominal 35 watts One or two 26 Volts AC 400 Hertz reference excitation inputs with a current requirement of less than 1 milliampere is required when the functions of AC synchro inputs or outputs are required for use with peripheral equipment This reference excitation signals must be obtained from the aircraft inverter source A third inverter input Datum Excitation is available specifically used in situations where the autopilot uses an additional inverter or the autopilot inverter frequency is higher than 400Hz The following section describes the technical characteristics that include the appliance approval basis physical and electrical properties electrical connector pin allocation which details function and gradient or equipment protocol and ARINC label support Also included is the description of the SN3500 installation components other equipment and installation requirements A review of the installation approval procedures is provided for filing with authorities 2 2 Part Numbers The part number for the standard Sandel SN3500 is SN3500 XXX Major Minor Variation Variation The part number for the Sandel SN3500 with NVIS support is SN3500 XXXN Major Minor Variation Variation The current version of software is displayed on the power up screen 82005 IM K Sandel SN3500 Installation Manual Page 2 1 Technical Information 2 2 1 Installation Kit and
145. to the proper pins and nowhere else Completed Comment Install the SN3500 into the clamp tray and verify full connector mating and that the unit installs without obstruction Completed Comment Activate the aircraft master switch and avionics master switch if installed Verify that the SN3500 display illuminates within 30 seconds Switch on all equipment interfaced to the SN3500 such as NAV receivers gyros and marker beacon receivers Completed Comment System Configuration If not previously accomplished perform the Post Installation Procedures included in the Appendix of the SN3500 Installation Guide These procedures describe how to configure the SN3500 for compatibility with installed systems Completed Comment System Functions Compass System Interface Power up the system and verify that within 3 minutes the compass card is displayed in white and agrees with the heading on a magnetic compass Completed Comment Disable the fluxgate excitation to the SN3500 Verify that within 10 seconds the compass digital heading is flagged Restore the fluxgate excitation and verify that within 10 seconds the display is fully restored Note If fluxgate excitation and gyro are interconnected remove both signals simultaneously and look for simultaneous failure indications Completed Comment Sandel SN3500 Installation Manual Page 11 4 11 1 8 82005 IM K Appendix E Checkout Procedures Remove power to or otherwise disabl
146. ttempt to discern any audible interference cause by the SN3500 Completed Comment Repeat for the secondary navigation radio Completed Comment Transmit on the frequencies 118 000 MHz 126 975 MHz and 135 975 MHz on the primary communications radio and attempt to discern any changes in the SN3500 display Completed Comment Repeat for the secondary communications radio Completed Comment 11 2 2 General Testing Observe any unusual interaction between the transponder DME ADF or Marker Beacon receivers and the SN3500 when switching power to any equipment Completed Comment 82005 IM K Sandel SN3500 Installation Manual Page 11 11 Appendix E Checkout Procedures 11 2 3 Additional Testing Perform any additional EMI RFI related tests deemed necessary Completed Comment 82005 IM K Sandel SN3500 Installation Manual Page 11 12 Appendix E Checkout Procedures 11 3 Operational Flight Test Procedures Report The following Operational Flight Check Procedures Report is for the purpose of simplifying the in flight operational check of the SN3500 A copy of this report and the Functional Ground Test Procedures Report must be retained by the installing agency and a copy must be installed in the aircraft maintenance records A copy must also be forwarded to Sandel Avionics along with the Warranty Registration Form Part Number 10235 which should be mailed after operational acceptance 82005 IM K Sandel SN3500 Installa
147. ture Altitude 20 C to 70 C up to 55 000 feet Power Inputs 22 to 33 Vdc 40 watts maximum at startup for Lamp units 33 watts maximum at startup for LED units 11 to 33 volts DC on units with serial number 5 2500 or higher 27 5 Vdc 1 4A nominal 38 5 watts Lamp Units 27 5 Vdc 1 2A nominal 33 watts LED Units 14 0 Vdc 2 4A nominal 33 watts LED Units 2 5 Connector Summary The SN3500 was designed to interface and operate with several generations of avionics equipment It is compatible with DC analog and or ARINC standard synchro and serial digital signals as well as industry standard and adopted AC and DC sine cosine and discrete input and output voltages The SN3500 design and operation is optimized for efficient adaptability to both new and existing avionics equipment and systems The lists on the following pages reflect the configurable input and output signal types for various equipment types See SETUP PROCEDURES on page 4 1 for more information on maintenance setup pages IMPORTANT Connectors P1 and P2 are not interchangeable Damage to the SN3500 may result if the connectors are reversed 82005 IM K Sandel SN3500 Installation Manual Page 2 5 2 5 1 Connector P1 Technical Information Pin Name Signal Type dependent on maintenance page selection 16 Inverter In Note May be same or different than P2 16 inverter source Inverter 26Vac
148. vailable P2 19 WHF Nav2 ILS Energize Input Control the enabling of the Vertical Deviation Bar when NAV2 selected P2 35 VHF NAV2 429A Composite P2 21 VHF NAV2 429B Primary 429 input from VHF NAV2 or composite input from analog receiver for VOR bearing pointer Composite is normally 5v VOR 33v LOC For 3V inputs a series resistor is required see the installation drawings When using the composite input for LOC deviation the calibration procedure found in section 7 1 5 must be followed for each specific LOC input 24 AWG shielded wire is recommended for these connections Note When using the composite signal for the localizer deviation input the calibration procedure found in section 7 1 5 must be performed after the installation prior to release for flight P2 6 DME1 Data Analog DME DC 429A P2 36 DME1 CLK Analog DME DC 429B P2 22 DME1 Sync P2 7 DME1 Hold Serial data inputs for either ARINC 429 568 serial protocols to support ARINC DME s as selected within the DME Maintenance page Low speed only Bendix King DME s using King Serial Digital protocol See the installation drawings 24 AWG twisted shielded triple conductor is required for these functions Note This is DME1 Analog DME input 40mV mile may also be used P2 37 OBS Resolver DC ref Input P2 23 OBS Resolver H Input P2 8 OBS Resolver SIN Output P2 38 OBS Resolver COS Output OBS resolver connections for NAV or GPS receivers The input frequency
149. will appear as prompts C Escape the maintenance menus by pressing and holding the course pointer knob left knob This will allow normal operation of the unit to test the effects of settings Re enter the maintenance pages pressing and holding the course pointer knob left knob D To disable maintenance menu operation power down and restart normally All configured items are stored in non volatile memory 4 3 Equipment Configuration Selections The choices of compatible equipment contained in the SN3500 menus are listed in the Appendix For types not listed consult the factory 82005 IM K Sandel SN3500 Installation Manual Page 4 1 Operating Details 5 Operating Details For an explanation of the operating details of the SN3500 refer to the Pilot s Guide for the SN3500 Sandel Avionics P N 82005 PG and to the Airplane Flight Manual Supplement The SN3500 may utilize either an LED light source or a lamp light source The pilots guide P N 82005 PG revision F or later should be referenced for light source identification and applicable data color coding information 82005 IM K Sandel SN3500 Installation Manual Page 5 1 Instructions For Continued Airworthiness 6 Instructions For Continued Airworthiness 6 1 General The following is a summary of the Instructions for Continued Airworthiness prepared under the guidelines of FAA Advisory Circulars 23 1309 1 and 25 1309 1 which identifies potential failure modes of t

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