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Garmin SA01933LA_D Instruction Manual

1. Arrangement pounds pounds pounds pounds 100 inch Drawing pounds Instrument Panel Instruments and x x Avionics Stack GRS 77 x GDC 74A X X GAD 43 X GA 35 X GMU 44 X X GTP 59 X Transponder x Antennas DME Antenna X WSI Antenna xX There is no specified discard interval for fasteners Fasteners must be discarded if threads or heads become stripped 2 12 Special Tools For electrical bonding testing a milli ohm meter is required Tools specific to GTX 330D transponder maintenance e TIC TR 220 or Equivalent Multi function Ramp Tester supporting transponder Modes A C S Pitot Static Ramp Tester 3 32 Hex Tool 4 Screwdriver Windows compatible PC computer Only required for software loading purposes laptop is preferred 2 13 Additional Instructions There are no additional ICA instructions for this STC 2 14 Overhaul Period The G600 system does not require overhaul at a specific time period Power on self test and continuous BIT will monitor the health of the G600 system Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 24 of 29 The GNS 530W and GNS 430W do not require overhaul at a specific time period Power on self test and continuous BIT will monitor the health of the unit The GMA 347 does not have any additional overhaul time limitations The GMX 200 and WSI AV 200 do not require overhaul at a sp
2. SOFT SOLDER XK KX lt oo N gt 7 CABLE INSULATOR 5 Tin the center conductor then solder the contact onto the center conductor butting the contact up against the cable insulator Do not exceed specified solder temperatures in Table A 1 6 Flair the outer shield braid by gently rotating the contact and dielectric then finish to flare out taking care not disturbing the inner foil shield Do not remove the inner foil shield from the dielectric 7 Insert the contact into the rear of the connector body The inner shield goes inside of the connector body and the braid shield goes outside until the contact snaps into place Slide the crimp tube up over the braid and up against the connector body Crimp using tooling specified in Table A 1 8 Install black adhesive heat shrink into place past crimp tube and up over connector body and heat shrink into place 9 Reattach the connector to the corresponding transponder antenna or transponder rack 10 Perform function checks as specified in section 2 5 1 A 2 DME Cable Connectors Table A 2 lists required tooling to accomplish the termination Table A 2 DME Cable Tooling Item Description Part No Hex Die Tooling Military P N M22520 5 43 Or Daniels P N Y141 Tool Frame M22520 5 01 HX4 Hex Size A Hex Solder Temp 700 750F Termination Instructions Ref Emteq Dwg ES 105 1 1 Disconnect faulty connector from DME
3. Maintenance Data or later revisions e 005 00368 12 Avionics Installation GNS 530 W GMX200 WSI AV 200 150 Rev 8 e 005 00368 13 Avionics Installation GNS 530 W GMX200 WSI AV 200 250 Rev 9 190 00607 04 GMX 200 Installation Manual Rev B WSI 305427 00 WSI AV100 AV 200 Installation Manual STC SA01512WI D Maintenance Data or later revisions Retention 005 00521 13 DME Antenna Reassignment Cessna 208 208B Rev 6 005 00521 14 Avionics Bus 1 Switch Breaker Modification Cessna 208 208B Rev 2 This document or the information contained within will be included in the aircrafts permanent records J e e 005 00521 11 GTX330D Antenna Installation in Cessna 208 208B Rev 5 e J Instructions for Continued Airworthiness G600 GNS 530W GNS 430W GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B 190 01080 05 Rev 2 Page 4 of 29 2 2 Description of Alteration This STC upgrades existing avionics for the Cessna 208 208B Caravan as summarized below Equipment locations are identified in Figure 1 below GRS 77 AHRS 2X GAD 43 ADAPTER GDC 74A AIR DATA COMPUTER GMA 347 GMX 200 GNS 530W GNS 430W TRANSPONDER 2 GTX 330D ES 2X ANTENNA GDU 620 PFD MFD GTP 59 TEMPERATURE PROBE GA 35 GPS ANTENNAS TOP VIEW GMU 44 MAGNETOMETERS TOP TRANSPONDER WSI ANTENNA DME ANTENNA AS REASSIGNED PER STC SIDE VIEW Figure 1 Equipment Locations C208B as show
4. Months Friction and vi Barometric Scale Error are not applicable because the digital outputs of the GDC 74A are not susceptible to these types of errors Conduct a visual inspection of the antennas and their mounting Verify there are no cracks on the antenna no cracks or deformation in the mounting structure around the antenna and GA 35 GPS that all sealing fillets around the antennas are in good condition Antennas 12 Calendar CI 1530 1 WSI If the antenna is broken cracked or dented it must be replaced Months 1 Antenna If the attachment is not secure or the antenna seal shows signs of damage or decomposition re attach antenna as described in section 2 7 7 2 GA 35 antenna or section 2 7 10 2 WSI antenna Conduct a visual inspection look for signs of wear deterioration or damage to wires backshells or connectors on units and their GDU 620 Sean mas wire harnesses to ensure installation integrity GRS 77 1 Gain access to LRU see General Arrangement Drawing GDC 74A for LRU locations GMU 44 l 2 Inspect each unit for security of attachment 12 Calendar GTP 59 ae GAD 43 3 Inspect all knobs and buttons for legibility Months 1 4 Inspect condition of wiring routing and GNS 530W attachment clamping GNS 430W a ai 5 Inspect integrity of shield terminations GMA 347 6 Inspect for signs of corrosion on equipment and rack installations Instructions for Continued Airworthines
5. The GMA 347 is connected to a previously installed marker beacon antenna A GMA 347 maintenance connector PG11 is installed behind the pilot s instrument panel for connection when performing configuration or software updates GMX 200 Multifunction Display and WSI AV 200 The Garmin GMX 200 multifunction display is located in the radio stack in the center instrument panel displaying information from the GNS 530W WSI AV 200 weather datalink receiver and airborne weather radar RDR 2000 radars only A remote mounted WSI AV 200 with Comant Cl 1530 1 WSI Low Profile Satellite Antenna is installed and provides datalink weather information to the GMX 200 multifunction display GTX 330D ES Transponders Two Garmin GTX330D ES Mode S diversity transponders with ADS B Out are installed in the radio stack in the center instrument panel Four Comant Cl 105 L Band antennas are also installed Two antennas are required for each GTX330D one mounted on the top and the other on the bottom of the aircraft for a total of four antennas for the installation Only one GTX330D can be active at a time A XPDR 1 2 select switch allows the crew to toggle between GTX330D 1 and 2 The switch state determines which GTX330D is the active transponder Transponder maintenance connectors are installed below the instrument panel for easy connection when performing software updates The GNS 530W and GNS 430W outputs GPS data including GPS groundspeed altitude latitud
6. 208 208B Page 20 of 29 2 Rotate the Allen wrench counterclockwise until the front lobe of the locking mechanism is in a vertical position 3 Slide the unit into its rack until the front lobe of the locking mechanism touches the rack 4 Rotate the Allen wrench clockwise until the unit is secured in its rack NOTE Do not over tighten Do not force the unit in if installation is obstructed Instead remove the unit and determine the source of obstruction before reattempting installation Original GTX330D is reinstalled e Perform the GTX Regulatory Testing specified in section 2 5 1 NOTE No software or configuration loading is required if the removed GTX is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process New Repaired or Exchange GTX330D is Installed e Complete all software verification and configuration procedures in accordance with Section 4 of the appropriate Modification Summary e Perform the GTX Regulatory Testing specified in section 2 5 1 2 7 12 Top Transponder Antenna Removal amp Replacement NOTE Refer to the Antenna Installation Drawing 005 00521 11 for diagrams specific instructions and installation data related to the transponder antenna installations 1 Gain access to the upper antenna installation by removing the interior cargo liner Refer to the Cessna Caravan Maintenance Manual D2078 21 13 for t
7. Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 19 of 29 Configure the GMA 347 in accordance with Section 4 of the applicable Modification Summary 2 7 8 3 Return to service Perform a Transceiver Operational Check as described in Section 5 of the applicable Modification Summary 2 7 9 GMX 200 2 7 9 1 Removal Insert a 3 32 inch hex drive tool into the access hole on the unit face Unscrew the screw shaft The unit will be loosened and then may be pulled from the tube No special extraction tools are required 2 7 9 2 Installation Slide the unit into the tube and hand tighten the threaded screw shaft using a 3 32 hex The unit will be pulled into the tube by the shaft and the connectors will fully engage The back of the bezel must be flush to the mounting tube Original GMX 200 is reinstalled Verify that the unit power up self test sequence is successfully completed and no failure messages are annunciated No configuration is required Replacement or repaired GMX 200 is installed Verify software version and perform post installation checkout procedures in accordance with the applicable Modification Summary No configuration is required GMX 200 Configuration Module is Replaced If the GMX 200 Configuration Module is replaced then the configuration setup will need to be performed Refer to Section 4 of the appropriate Modification Summary for GMX 200 configurat
8. GA 35 GPS connector and a nearby exposed portion of aircraft ie 10 years Antennas structure example exposed rivet on fuselage stringer veal ve whichever is 4 Verify the resistance is equal to or less than 5 milliohms first 5 Reconnect the coaxial cable to the antenna connector and ensure it is secured Repeat for second GA 35 Antenna In the event of bonding test failure remove antenna clean and re attach using the procedures in Section 2 7 7 The GTX 330D transponders must be tested and shown to A Tesini comply with 14 CFR Part 91 411 91 413 and Part 43 Appendix E ena 9 y 9 and F as described in section 2 5 1 GTX 330D The GTX 330D transponders must be shown to comply with 14 slo ace rent GNS 530W or ADS B Out Testing CFR Part 91 227 as described in section 2 5 2 GNS 430W GTX 330D and A visual inspection of the GTX 330D transponders and Cl 105 12 Calendar Cl 105 Antennas antennas must be performed as described in section 2 5 3 Months 1 Every 2000 GTX 330D and Cl 105 Antennas An electrical bonding test of the GTX 330D transponders and Cl 105 antennas must be performed as described in section 2 5 4 flight hours or ten 10 years whichever is first Notes 1 Complete within the preceding 12 calendar months as part of an annual or progressive inspection program This inspection interval may be extended to within the preceding 24 calendar months for aircraft that are inspected in accordance with other a
9. against connector body Crimp using the tooling specified in Table A 1 9 Affix the o ring to the access cap thread the access cap onto the connector body and tighten Install black adhesive heat shrink into place past crimp tube and up over connector body and heat shrink into place 10 Reattach the connector to the corresponding transponder antenna 11 Perform function checks as specified in section 2 5 1 Termination Instructions 180 Connector Ref Emteq Dwg ES 105 7 1 Disconnect faulty connector from lower transponder antenna or transponder rack Cut the connector off completely using snips or diagonal cutters Make every attempt to limit the amount of cable which is removed along with the connector NOTE For proper transponder diversity performance all four cables must be within 12 inches total length of each other 2 Slide on heat shrink label black adhesive heat shrink and crimp tube Installer is responsible for remaking cable labels Use existing cable label as a reference 3 Strip the cable insulation according to the following diagram 0 775 19 68nnJ 045 0 300 12 07nn 7 62nn 0 420 pro 10 67nm SoS Ezzzz777 4 Install cable insulator onto center conductor butting it up against cable dielectric as shown Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 27 of 29
10. the repair testing process Recalibration is only required if the mount for the magnetometer was Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 16 of 29 changed If the magnetometer mount was changed refer to Section 4 of the appropriate Modification Summary for the GRS 77 GMU 44 Magnetic Calibration New Repaired or Exchange GMU 44 is Installed If the GMU 44 was replaced with a new repaired or exchanged unit then software must be loaded and the GRS 77 GMU 44 Magnetic Calibration must be performed Refer to Section 4 of the appropriate Modification Summary for more information for instructions on loading software and Magnetic Calibration 2 7 3 3 Return to Service After removing and reinstalling the GMU 44 the following return to service checks should be performed 1 Power up the G600 system with the GDU 620 in normal mode 2 Verify that the GDU displays valid heading within approximately one minute NOTE The heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large ground power cart 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Appendix A of the appropriate Modification Summary 2 7 4 GDC 74A 2 7 4 1 Removal 1 Gain access to the GDC 74A see General Arrangement Drawing for location 2 Disco
11. 0 Configuration Module is Replaced If the GDU 620 Configuration Module is replaced the GDU 620 will update the configuration module from its internally stored settings when the UPDT CFG soft key is pressed If the GDU 620 is replaced at the same time as the Configuration Module then the System Setup will need to be performed Refer to Section 4 of the appropriate Modification Summary for more information 2 7 1 3 Return to Service After removing and reinstalling the GDU 620 per the instructions above a simple return to service check should be performed 1 Power up the GDU 620 and all interfaced systems in normal mode 2 Verify that there are no red Xs and that no alerts are present If red Xs or alerts are present troubleshoot using Appendix A of the appropriate Modification Summary 2 7 2 GRS 77 2 7 2 1 Removal 1 Gain access to GRS 77 See General Arrangement Drawing for location 2 Disconnect the GRS 77 connector 3 Loosen the four Phillips thumbscrews with a screwdriver 4 Gently lift the GRS 77 from the mounting plate if the supports for the mounting plate are removed the GRS 77 must be recalibrated 2 7 2 2 Installation 1 Place the GRS 77 on the mounting plate ensuring the orientation is correct 2 Fasten the unit to the plate using the Phillips thumbscrews Recommended torque is 22 25 inch pounds 3 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 4 Connect the conne
12. Instructions for Continued Airworthiness G600 GNS 530W GNS 430W GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Dwg Number 190 01080 05 Rev 2 NOTE This document supersedes 190 00694 00 ICA GNS 530W GMX 200 and WSI AV 200 in Cessna C208 C208B from prerequisite STC SA01712SE D NOTE This document supersedes 190 00544 50 Dual GTX330Ds in Cessna 208 Caravan Post Installation Checkout amp ICA from prerequisite STC SA01512WI D Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA Record of Revision Rev Date Description of Change 01 25 10 Initial Release 2 05 21 14 Added maintenance data from prerequisite installations and updated maintenance data for the G600 GNS 430W 530W GMX 200 GMA 347 and GTX 330D Transponders ee TABLE OF CONTENTS dee introd ctiofssser ncteety ceataid a tater a taut torte ania tau tpiant Ace ean N ANS 3 1 1 PU DOSE axcnsd sisi a a n E T E mei amen name arena E E 3 1 2 BIE ea E ads pen T E E E E udeh tpiams A E AA 3 2 Instructions for Continued Airworthiness cc ecssessescceseseesceceseseesceceaescesesceaseeeeneeaseeeneneaeees 4 2 1 LPFOGUIGIIGMN s35 sctbsssnctcedasancewss A A AEAEE 4 2 2 Description of Alteration iens a a a a E A aa ih 5 2 3 Control Operation Information s s ssesssesesesesesesesssseseseseseststtesestseststsesesesssstsesesesesenernesesesese 7 Pae E E 11010 EENEI ERE E A E E E E A 7 232 GNS SBOV U
13. TA S OWN eee eene eir EE E e ARE A E A EE celebs E A EE e 7 23 9 GMA SAT r ee busses van a A V Ea A E aad TTS 8 2 3 4 GMX 200 and WSI AV 200 csi cssconssibsusvesnna hs slater macdacontecvstiidy cubesnne alaluenecancantecvatodiecpheonkias 9 23 9 NT II BS OU yest ec Bot ets States See Adalat ie BN A lesa ete 9 2 4 Servicing IMTORMALOMS ees ene reeniras rens aee r n eten EE EE OEE r neia LA snares 10 2 5 Periodic Maintenance Instructions sc sesstaveticctarinuae eetearieaten pd annette 10 2 5 1 GTX 330D Regulatory Testing 241 t vessasitesvasicossdsaiess anacesbeasetdagvigacovesanederooadiobescsider sence 12 2 5 2 GTX 330D ADS B Out Testing sess ccisnsisoncssiseiecleviceas ea tend icasnedinentmn ais nawteneawee 12 2 5 3 GTX 330D Installation Visual Inspection 25 240 cex cecccesendcccevekeraveuntarenenvaivesdvenivavedouncaodenten 13 2 5 4 GTX 330D Installation Electrical Bonding TeSt eee eceeseeeeeeseseeeeseeeeseeeeeeeeeaeeeeaes 13 2 6 Troubleshooting ITOFMABION j lt sica02 hetacalprssdavisedscayinattaseipuaaeeisete nd taea mane totic eas 14 2 7 Removal and Installation Information ee eecesseseeeescsseseeecseceseeecseeeeseeecaeeeeseeecaeeaeeeeeeneeas 14 ELAN ASSIS Osos cxscccsatdet toy nbs E eaves uo meagan eared panies detonate amen este canta uo let A acy wea ao aE uae 14 Zl 2 AAO TA ceases ened a E E A E ec ateat deve E a osaiea heated tee 15 23 GMU MA sentence A e vee A ON TS EG ae Loam aT VRS 16 ZEA NG LA eani sins iee aE E Ee sud
14. age 9 of 29 2 4 Servicing Information In the event of a G600 system GNS 530W GNS 430W GMA 347 or GTX 330D failure troubleshoot the unit s in accordance with Appendix A of the appropriate Modification Summary In the event of a GMX 200 or WSI AV 200 failure troubleshoot the unit s in accordance with the Installation Manual for that unit The Garmin GA 35 GPS Antennas Comant Cl 105 Transponder Antennas and Comant Cl 1530 1 WSI Antenna are non repairable in the event of a failure the antenna must be replaced 2 5 Periodic Maintenance Instructions Maintenance of the components installed by this STC is on condition except as noted in the following table Item Description Procedure Interval The GRS 77 utilizes an Earth magnetic field model which is updated approximately every five years as part of the Aviation Database maintained by the owner operator If the magnetic model is not current the unit will issue an alert upon startup i ORS TT AMRS indicating the model has expired The model can be updated by On conaion inserting an aviation database card in the GDU 620 with an updated IGRF model and powering on the system A prompt will direct the user to press ENT to update the model Test according to 14 CFR Part 91 411 and Part 43 Appendix E See the pitot static checkout procedure in Section 5 of the appropriate modification summary document 24 Calendar GDC 74A ADC The tests of Part 43 Appendix E sub paragraphs iv
15. attached If there is visible sign of damage to the antenna then it must be replaced The GTX 330D receiver sensitivity must be tested and shown to comply with Title 14 CFR Part 43 Appendix F as described in section 2 5 1 If the antennas were damaged to the point where any piece or fragments of the antenna departed the aircraft then an inspection of the airframe and control surfaces shall be performed to ensure that there was no damage from debris impacting the airframe 2 9 1 4 DME Antenna The Transponder antennas and the surrounding installation shall be inspected to ensure that there is no structural damage around the areas where lightning may have attached If there is visible sign of damage to the antenna then it must be replaced The DME shall be tested by using the transponder DME ramp tester 2 9 2 Special Inspection Techniques There are no special inspection techniques required 2 10 Application of Protective Treatments Not applicable Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 23 of 29 2 11 Data Relative to Structural Fasteners Refer to the following table for data on the location type and torque values for structural fasteners FASTENER TYPE AND TORQUE Location 6 32 Screw 8 32 Screw 8 32 Nut 10 32 Screw NUT 5 16 see General 12 15 inch 12 15 inch 12 15 inch 22 25 inch HEX SKIRT
16. ctor to the GRS 77 ensuring that each slidelock is secured on both sides Original GRS 77 is Reinstalled If the original GRS 77 is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Reference Table 2 1 to determine whether recalibration is required New Repaired or Exchange GRS 77 is Installed Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 15 of 29 If the GRS 77 is replaced with a new repaired or exchange unit then software must be loaded per Section 4 of the appropriate Modification Summary Reference Table 2 1 to determine whether re calibration is required GRS 77 Configuration Module is Replaced If the GRS 77 Configuration Module is replaced the GRS 77 must be re calibrated Reference Table 2 1 2 7 2 3 Return to Service After removing and reinstalling the GRS 77 the following return to service checks should be performed 1 Power up the G600 system with the GDU 620 in normal mode 2 Verify that the GDU displays valid heading and attitude within approximately one minute NOTE The Heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large ground power cart 3 Verify that no unexpected alerts are pr
17. des Set the GDU 620 into place 3 Install the six mounting screws into the bezel of the GDU 620 NOTE The installation configuration settings are stored in the configuration module and will be retained when the GDU 620 is replaced with a new unit User settings such as map orientation preferences are stored internally and will be lost when the GDU 620 is replaced with a new unit Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 14 of 29 Original GDU 620 is Reinstalled If the original GDU 620 is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process No configuration is required New Repaired or Exchanged GDU 620 is Installed If the GDU 620 is replaced with a new repaired or exchange unit then software must be loaded No configuration is required NOTE Upon first power up after installing a new GDU 620 it is normal to see a series of O LOADING messages appear on the screen These messages indicate that the GDU 620 is updating its configuration settings from the configuration module Continue to the GDU 620 Software Loading procedure followed by the Manifest Configuration and the Configuration Module Update located in Section 4 of the appropriate Modification Summary GDU 62
18. des information required by the operator to adequately maintain the Garmin G600 Avionics Display System Garmin GNS 530W GPS NAV COM Garmin GNS 430W GPS NAV COM Garmin GA 35 GPS Antennas Garmin GMA 347 Audio Panel Garmin GMX 200 WSI AV 200 Comant Cl 1530 1 WSI Antenna Garmin GTX 330D ES transponders and Comant Cl 105 Transponder Antennas when installed under the following STCs STC Number Description SA02017SE D Installation of the G600 GNS 430W GA 35 GPS Antenna and GMA 347 Requires installation of SA01712SE D and SA01512WI D as prerequisites SA01712SE D Installation of the GNS 530W GA 35 GPS Antenna GMX 200 WSI AV 200 and Cl 1530 1 WSI Antenna SA01512WI D Installation of dual GTX 330D ES transponders and Cl 105 Transponder Antennas 1 2 Definitions The following terminology is used within this document AC Advisory Circular ACO Aircraft Certification Office ADC Air Data Computer AEG Aircraft Evaluation Group AHRS Attitude Heading Reference System CFR Code of Federal Regulations FAA Federal Aviation Administration GPS Global Positioning System ICA Instructions for Continued Airworthiness LRU Line Replaceable Unit GTS computer Antenna or PA LNA MFD Multi Function Display OAT Outside Air Temperature PFD Primary Flight Display PMI Principal Maintenance Inspector STC Supplemental Type Certificate TSO Technical Standard Order TVS Transient Voltage Sup
19. e longitude track and position integrity to both GTX330D transponders over an RS 232 serial data bus The GTX330D only transmits ADS B messages and cannot receive and process ADS B messages Avionics Bus 1 Switch Breaker Modification On Caravan aircraft equipped with KFC250 autopilots the Avionics Bus 1 switch breaker is required to be upgraded from the existing 20 amp unit to a new 30 amp unit This upgrade is optional for KFC150 equipped Caravans to be used for installations which require additional electrical margin DME Antenna Re assignment The existing transponder 2 antenna location on pre modification aircraft is located on the cargo pod aft left side This antenna remains installed and becomes the DME antenna The two forward most L Band antennas under the cargo pod are replaced with new Comant Cl105s and become transponder 1 left side and transponder 2 right side antennas respectively A new low loss DME coaxial cable is also installed Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 6 of 29 2 3 Control Operation Information 2 3 1 G600 System The GDU 620 GRS 77 GMU 44 and GDC 74A are powered by Main Bus 2 which is normally energized with battery generator or external power applied to the aircraft The GAD 43 is powered by Avionics Bus 1 which is normally controlled by the Avionics Bus 1 master switch The LRUs do not
20. e powered on 3 If the transponders are configured for pilot control of the ADS B transmitter press the FUNC key until ADS B TX is displayed and ensure that ADS B TX is ON for both transponders press the START STOP key to toggle between ON and OFF 4 Select XPDR 1 using the transponder selector switch 5 Remove power from the GNS 430W by pulling the NAV 2 circuit breaker Ensure the GNS 530W is operating normally and has acquired a GPS position 6 Temporarily configure XPDR 1 into airborne mode as follows a Start XPDR 1 in configuration mode hold the OFF key to power down the unit then hold the FUNC key and press the ON key b Press the FUNC key until the SQUAT SWITCH page is displayed Then use the CRSR and 8 9 keys to change the setting to YES and the SENSE to LOW Press the CRSR key until no fields are highlighted to save the changes 7 Restart XPDR 1 in normal operating mode and select ALT mode 8 Using the transponder test set verify the following ADS B Out parameters are being transmitted e NACv value of 1 or greater Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 12 of 29 10 11 12 13 14 15 2 5 3 SDA value of 2 lt 1x10 5 SIL value of 3 lt 1 x10 7 NACp value of 8 or greater NIC value of 7 or greater eset the XPDR 1 squat switch configuration a
21. ecific time period The GTX 330D transponders do not require overhaul at a specific time period 2 15 ICA Revision and Distribution To revise this ICA Garmin will follow the Garmin ODA procedures manual SOP 0055 ACP 0016 for Instructions for Continued Airworthiness The latest revision of this ICA document is available on the Garmin website www flyGarmin com To Access Aviation Manuals select the Support tab and then select Manuals You may also contact Garmin General Aviation Product Support at 866 739 5687 US toll free 913 397 8200 or avionics garmin com 2 16 Assistance Flight Standards Inspectors or the certificate holder s PMI have the required resources to respond to questions regarding this ICA In addition the customer may refer questions regarding this equipment and its installation to the manufacturer Garmin Garmin customer assistance may be contacted during normal business hours via telephone 913 397 8200 or email from the Garmin web site at www garmin com 2 17 Implementation and Record Keeping Modification of an aircraft by this Supplemental Type Certificate obligates the aircraft operator to include the maintenance information provided by this document in the operator s aircraft maintenance manual and or the operator s aircraft scheduled maintenance program 3 Airworthiness Limitations There are no additional Airworthiness Limitations as defined in 14 CFR Part 23 Appendix G G23 4 that result from
22. enter configuration mode on the GMX 200 immediately after the self test is complete press line select keys 1 4 and 6 in sequence before pressing any other keys where 1 is the top line select key 4 is the fourth key down and 6 is the lower most line select key Refer to the appropriate Modification Summary Section 4 for further Configuration instructions 2 3 5 GTX 330D The 1 GTX330D receives power from Avionics Bus 1 and the 2 GTX330D receives power from Avionics Bus 2 The GTX 330D starts in normal mode when power is applied to the unit To enter configuration mode apply power to the GTX 330D while holding the FUNC key then press the ON key to access the configuration pages In order to perform maintenance tasks such as software updates and other diagnostic activities a Windows compatible PC computer preferably a laptop is required The maintenance port is located below the instrument panel just immediately behind the throttle quadrant as shown in 190 01080 00 Install Dwg 150 G600 GNS430W GMA347 Cessna 208 208B and 190 01080 01 Install Dwg 250 G600 GNS430W GMA347 Cessna 208 208B CAUTION The GNS 430W must be powered off prior to programming transponders via the maintenance port Refer to the appropriate Modification Summary Section 4 for further Configuration instructions Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B P
23. esent If alerts are present troubleshoot using Appendix A of the appropriate Modification Summary Table 2 1 GRS 77 Calibration Criteria Calibrations Required GRS 77 GRS GMU Engine Run up Pitch Roll Magnetic Vibration Condition Offset Calibration Test See Section 4 of See Section 4 of See Section 4 of Modification Modification Modification Summary Summary Summary GRS 77 AHRS was removed and or replaced The mounting tray was NOT removed and the mounting tray bolts were NOT loosened GRS 77 AHRS was removed and or replaced The mounting tray WAS removed and or mounting tray bolts WERE loosened GRS 77 AHRS Configuration Module was replaced None Required 2 7 3 GMU 44 2 7 3 1 Removal Gain access to the GMU 44 magnetometer see General Arrangement Drawing for location Unscrew the three screws that hold the GMU 44 to its mounting rack Carefully lift the GMU 44 from the rack 4 Disconnect the wiring harness 2 7 3 2 Installation G2 IN Se 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Connect the wiring harness to the GMU 44 3 Lower the GMU 44 into the rack and secure the plate with the three Phillips screws Original GMU 44 is Reinstalled If the original GMU 44 was reinstalled then software loading is not required This does not include units that were returned for repair as their software and configuration files are deleted during
24. for integrity a Verify the racks fasteners and support structure are in good condition and are securely fastened Inspect the condition of the wiring harnesses and coaxial cables a Verify that all wiring and cables are securely fastened b Verify that the harness shows no signs of cracking chaffing abrasion melting or any other form of damage Cargo Pod Interior Inspect both lower transponder antenna locations remove Isocryl tape sealant from antenna stud holes in cargo pod a Verify the antenna and ground plane fasteners are secure b Verify no moisture or corrosion is present c Verify no visible delaminating of composite structure exists d Replace flexible Isocryl tape sealant into all antenna stud holes in accordance with the Antenna Installation drawing 005 00521 11 Fuselage Top Inspect the exterior top transponder antenna installations Diversity Systems only a Verify the antennas are securely fastened b Verify the sealant around each antenna base is in good condition c Verify there is no evidence of cracking or corrosion at the installation site Cargo Pod Exterior Inspect the bottom exterior transponder antenna installations a Verify the antennas are securely fastened b Verify the sealant around each antenna base is in good condition c Verify the antenna ground plane is securely attached to the cargo pod structure and that there are no signs of de lamination or looseness d Verify there is no evidence of crack
25. g 005 00521 11 Table 2 2 Transponder Coaxial Cable Information Item Manufacturer Description Part No Emteq 5349 S Emmer Drive New Berlin WI 53151 888 679 6170 PMA Approved Cable Assemblies P Ns BR19252BS 301 BR19252BS 501 BS19252BS 401 BS19252BS 601 Coax Cable Assy XPDR1 Top Coax Cable Assy XPDR2 Top Coax Cable Assy XPDR1 Bottom Coax Cable Assy XPDR2 Bottom Cable Type PFLX340 500 Length Specification 192 3 0 Inches NOTE Cable length difference shall not be more than 12 inches between all four transponder cables This is critical for proper transponder performance Impedance Attenuation 50 Ohm 6 11 dB 100 ft 1090 MHz Right Angle Connector P N Emteq BMR340 1 Straight Connector P N Adhesive Heat Shrink Emteq BMS340 1 RayChem ATUM 1 2 BLK For the DME coaxial cable install the cable following the requirements of the DME Antenna Reassignment Drawing 005 00521 13 Table 2 3 DME Coaxial Cable Information Item Description Part No Manufacturer Emteq 5349 S Emmer Drive New Berlin WI 53151 888 679 6170 PMA Approved Cable BS31277BS DME1 Assembly P N Cable Type PFLX240 500 Length Specification 312 Inches Impedance 50 Ohm Attenuation 8 79 dB 100 ft 1000 MHz Straight Connector P N Emteq BMS240 1 qty 2 Adhesive Heat Shrink RayChem ATUM 1 2 BLK Instructions for C
26. have individual power switches and are powered when the bus is energized and the circuit breakers are closed The following circuit breakers provide power to the individual LRUs e PFD GDU 620 AHRS 1 GRS 77 1 and GMU 44 1 AHRS 2 GRS 77 2 and GMU 44 2 ADC GDC 74A GAD GAD 43 The GDU 620 has a PFD left and MFD right display and front panel controls for performing all G600 normal and configuration operations Knobs at the lower left and right corners are used for selecting and entering data on each screen The function of the soft keys along the bottom of the display is depicted by the text above the key There are dedicated ENT CLR and MENU keys on the right side of the unit Turning the PFD knob adjusts the values for the mode selected by the PFD bezel keys such as Heading HDG Course CRS Altitude ALT Vertical Speed V S and Barometric Setting BARO The values are shown in a window to the left of the HSI Pressing the PFD knob reverts to the default value of the selected mode The Small Inner MFD Knob selects a specific page within a page group Pressing the small MFD knob turns the selection cursor ON and OFF When the cursor is ON data may be entered in the applicable window by turning the small and large MFD knobs In this case the large MFD knob moves the cursor on the page and the small MFD knob selects individual characters or values for the highlighted cursor location The Large Outer MFD Knob selects the MFD
27. he interior cargo liner in accordance with the Cessna 208 Maintenance Manual Bottom Antennas 1 Gain access to the lower antenna installation site within the cargo pod 2 Remove the lsocryl tape sealant from within the antenna stud holes in the cargo pod 3 Measure the resistance between the base studs of each antenna to an exposed portion of aircraft structure example exposed rivet on cargo pod former 4 Verify the resistance is equal to or less than 5 millionms 5 Reinstall the Isocryl tape sealant in accordance with the Antenna Installation Drawing 005 00521 11 2 6 Troubleshooting Information Refer to Appendix A of the appropriate Modification Summary for troubleshooting procedures for any of the LRUs of the G600 system GNS 530W GNS 430W GMA 347 and or GTX 330D units For the GMX 200 and or the WSI AV 200 troubleshoot the unit s in accordance with the Installation Manual for that unit listed in section 2 1 of this document 2 7 Removal and Installation Information 2 7 1 GDU 620 2 7 1 1 Removal 1 Remove the six mounting screws from the bezel of the GDU 620 2 Pull the GDU 620 far enough out from the instrument panel to access the three rear connectors 3 Disconnect the rear connectors 4 Remove the GDU 620 2 7 1 2 Installation 1 Visually inspect the connectors to ensure that there are no bent or damaged pins Repair any damage 2 Connect the rear connectors ensuring that each slidelock is secured on both si
28. he upper left corner COM 1 and NAV 1 circuit breakers on Avionics Bus 1 supply power to the GNS 530W GNS 430W The GNS 430W is powered by Avionics Bus 2 which is normally controlled by the Avionics Bus 2 master switch The GNS 430W also contains a power switch which is controlled by the COM Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 7 of 29 volume rotary knob near the upper left corner COM 2 and NAV 2 circuit breakers on Avionics Bus 2 supply power to the GNS 430W NOTE The following operating instructions are applicable to both the GNS 530W and GNS 430W The GNS is self contained with a single display and front panel controls COM and NAV volume is controlled via two small rotary knobs COM NAV frequency selection is controlled via the left dual concentric knobs Pressing the knob toggles between COM and NAV frequency selection There are individual COM and NAV frequency flip flop keys near the volume knobs The right dual concentric knobs are used for page selection and entering data The Small Inner knob selects a specific page within a page group Pressing the small knob turns the selection cursor ON and OFF When the cursor is ON data may be entered in the applicable window by turning the small and large knobs In this case the large knob moves the cursor on the page and the small knob selects individual characters or values fo
29. his procedure 2 Disconnect antenna coaxial cable by twisting the BNC connector CCW 3 Remove the 8 32 hex nut lock washer and flat washer from each of the two antenna studs located inside the fuselage and set aside 4 Onthe exterior side of the antennas carefully remove any RTV sealant which surrounds the base of the antenna 5 Remove the antenna from the aircraft Inspect the installation location including ground plane BNC connector coaxial cable and fasteners for corrosion or any other form of damage Repair any damage before proceeding in accordance with the Cessna Caravan Maintenance Manual D2078 21 13 and or the installation drawings listed in section 2 1 as applicable 6 Reinstall the antenna in accordance with the Antenna Installation Drawing 005 00521 11 7 Perform the regulatory transponder testing required in section 2 5 1 prior to returning the aircraft to service 2 7 13 Bottom Transponder Antenna Removal amp Replacement NOTE Refer to the Antenna Installation Drawing 005 00521 11 for diagrams specific instructions and installation data related to the transponder antenna installations 1 Within the cargo pod gain access to the lower antenna installation sites Remove the lsocryl putty sealant from the antenna stud holes in the composite structure 2 Remove the 8 32 hex nut lock washer and flat washer from each of the two antenna studs and set aside 3 On the exterior side of the antennas carefully
30. ing or corrosion at the installation site GTX 330D Installation Electrical Bonding Test Perform an equipment electrical bonding check All electrical bonding for this installation must be 5 milliohms DC resistance or less If the resistance is higher than 5 milliohms remove LRU clean bonding interfaces reinstall and re measure until 2 5 millionms or less is reached GTX330D Unit Racks and Connectors Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 13 of 29 a4 Disconnect all harness antenna connectors from the LRU 2 From behind the instrument panel measure the resistance from each of the GTX330D racks to a nearby aircraft primary metallic structure Verify the resistance is equal to or less than 5 millionms 3 From behind the instrument panel measure the resistance from each GTX330D connector to a nearby aircraft primary metallic structure Verify the resistance is equal to or less than 5 millionms 4 Reconnect all disconnected harness antenna connectors and ensure they are secure Top Antennas 1 Gain access to the upper antenna installation site by removing the interior cargo liner refer to the Cessna 208 Maintenance Manual D2078 21 13 2 Measure the resistance between the base studs of each antenna to an exposed portion of aircraft structure 3 Verify the resistance is equal to or less than 5 millionms 4 Reinstall t
31. ion instructions 2 7 10 WSI AV 200 and WSI Antenna 2 7 10 1 Removal To remove the WSI AV 200 or WSI antenna gain access to the unit see Avionics Installation GNS 530 W GMX200 WSI AV 200 150 P N 005 00368 12 13 For the WSI AV 200 loosen mounting screw and disconnect wiring then remove unit from mounting tray For the WSI antenna remove the sealant surrounding the antenna and the 4 screws that hold the antenna in place then disconnect the coaxial cable 2 7 10 2 Installation Installation of the WSI AV 200 is the reverse of removal To reinstall the WSI antenna 1 Clean the antenna doubler and aircraft skin of any existing sealant or other material 2 Secure the antenna using the 4 8 32 screws and torque to 12 15 inch pounds 3 Using sealing compound PS700 run a bead of sealant along the antenna where it meets the aircraft skin Ensure the antenna connectors do not become contaminated with sealant 4 Reconnect the coaxial cable to the antenna connector and ensure it is secure 2 7 11 GTX 330D 2 7 11 1 Removal 1 Insert the hex drive tool into the access hole on the unit face and rotate counterclockwise until the unit is forced out about 3 8 inch 2 Pull the unit straight out of the rack 2 7 11 2 Installation 1 Insert a 3 382 hex wrench into the access hole on the front panel Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna
32. n C208 similar BOTTOM TRANSPONDER ANTENNAS G600 System The Garmin G600 PFD MFD System consists of an instrument panel mounted GDU 620 display and remote mounted LRUs which provide data to the display The GDU 620 provides controls for the G600 system and a PFD and MFD in the pilot s primary field of view The remote mounted LRUs include dual GRS 77 AHRS dual GMU 44 Magnetometers one GDC 74A ADC one GTP 59 OAT probe and one GAD 43 Adapter The GDU 620 MFD displays weather radar information and provides status control of the Aircraft Data Acquisition System Plus ADAS engine trend monitor system Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 5 of 29 GNS 530W and GNS 430W GPS NAV COM The Garmin GNS 530W and GNS 430W GPS NAV COM units are located in the radio stack in the center instrument panel and combines controls a multi function display NAV and COM transceivers and a GPS WAAS navigator into each unit Data from the GNS 530W and GNS 430W are displayed on the GDU 620 The GNS 530W and GNS 430W installations includes two GA 35 antennas one for each GNS unit The GNS 530W and GNS 430W are connected to previously installed Nav and Com antennas GMA 347 Audio Panel The Garmin GMA 347 Audio Panel is a horizontally oriented panel mounted audio control panel marker beacon system and intercom which interfaces to external inputs
33. n approximately one minute 3 Verify that no unexpected alerts are present If alerts are present troubleshoot using Appendix A of the appropriate Modification Summary Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 17 of 29 4 Perform a leak check of the pitot static system and observe the airspeed altitude and vertical speed for proper operation 2 7 5 GAD 43 2 7 5 1 Removal 1 Gain access to the GAD 43 see General Arrangement Drawing for location 2 Disconnect the GAD 43 connector 3 Remove the six mounting screws 4 Carefully remove the unit 2 7 5 2 Installation 1 Place the GAD 43 in its mounting location and align its mounting holes with the nutplates beneath it 2 Insert the six mounting screws and tighten the screws to hold the GAD 43 in place 3 Inspect the connector and pins for damage Repair any damage 4 Connect the connector to the unit ensuring that each slidelock is secured on both sides Original GAD 43 is Reinstalled If the original GAD 43 is re installed then no software loading or configuration is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process New GAD 43 is Installed If the GAD 43 is replaced with a new repaired or exchange unit then software must be loaded to the unit and the configura
34. nnect the pitot static plumbing from the rear of the unit Disconnect the single connector 3 Loosen each thumbscrew on the hold down clamp and remove the clamp 4 Carefully remove the unit from its mount A 2 7 4 2 Installation Place the unit in the mounting tray Position the locking clamp and fasten using the thumbscrews Connect the pitot static plumbing Inspect the connector and pins for damage Repair any damage Fon gt 5 Connect the connector to the unit ensuring that each slidelock is secured on both sides Original GDC 74A is Reinstalled If the original GDC 74A is re installed then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process New GDC 74A is Installed If the GDC 74A is replaced with a new repaired or exchange unit then software must be loaded to the unit Refer to Section 4 of the appropriate Modification Summary for more information GDC 74A Configuration Module is Replaced If the GDC 74A Configuration Module is replaced the GDC 74A must be configured Refer to Section 4 of the appropriate Modification Summary for more information 2 7 4 3 Return to Service After removing and reinstalling the GDC 74A the following return to service checks should be performed 1 Power up the G600 system with the GDU 620 in normal mode 2 Verify that the GDU displays valid air data withi
35. onnector body Crimp using tooling specified in Table 5 7 8 Install black adhesive heat shrink into place past crimp tube and up over connector body and heat shrink into place 9 Reattached the connector to the DME or DME antenna as appropriate 10 Use the Transponder DME ramp test equipment to do a basic functional check of the DME Follow the ramp test equipment and DME manufacturer s instructions Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 29 of 29
36. ontinued Airworth GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B iness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 Page 22 of 29 2 8 Diagrams Refer to the installation drawings listed in section 2 1 for equipment locations and wire routing detail 2 9 Special Inspection Requirements 2 9 1 Post Lightning Strike Inspection In the event of a suspected or actual lightning strike to the aircraft the GA 35 Antennas GTP 59 OAT Probe Comant Cl 105 transponder antennas DME antenna and their associated installation shall be inspected 2 9 1 1 GTP 59 OAT Probe The probe and the surrounding installation shall be inspected to ensure that there is no structural damage around the areas where lightning may have attached If there is visible sign of damage to the probe then it must be replaced Verify that OAT is displayed on the GDU 620 PFD normally 2 9 1 2 GA35 WAAS Antenna The GA 35 antennas and the surrounding installation shall be inspected to ensure that there is no structural damage around the areas where lightning may have attached If there is visible sign of damage to the antenna then it must be replaced A GPS signal acquisition test shall be performed as described in Section 5 of the applicable Modification Summary 2 9 1 3 CI 105 Transponder Antennas The Transponder antennas and the surrounding installation shall be inspected to ensure that there is no structural damage around the areas where lightning may have
37. or DME antenna Cut the connector off completely using snips or diagonal cutters Make every attempt to limit the amount of cable which is removed along with the connector 2 Slide on heat shrink label black adhesive heat shrink and crimp tube Installer is responsible for remaking cable labels Use existing cable label as a reference 3 Strip the cable insulation according to the following diagram Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 28 of 29 0 577 14 66nn 0 312 0 265 7 92nn 6 73nn E Z r be 4 Install cable insulator onto center conductor butting it up against cable dielectric as shown SOFT SOLDER CABLE INSULATOR 5 Tin the center conductor then solder the contact onto the center conductor butting the contact up against the cable insulator Do not exceed specified solder temperatures in Table A 2 6 Flair the outer shield braid by gently rotating the contact and dielectric then finish to flare out taking care not disturbing the inner foil shield Do not remove the inner foil shield from the dielectric 7 Insert the contact into the rear of the connector body The inner shield goes inside of the connector body and the braid shield goes outside until the contact snaps into place Slide the crimp tube up over the braid and up against the c
38. or GNS 430W unit is installed in the rack by sliding it straight in until it stops about 1 inch short of the final position Insert the hex drive tool into the access hole at the bottom of the unit face Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit is firmly seated in the rack Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 18 of 29 Original GNS 530W or GNS 430W is Reinstalled No configuration is required Replacement GNS 530W or GNS 430W is installed If the GNS 530W or GNS 430W unit is removed for repair and reinstalled or if the unit is removed and replaced with a different unit then verify software and configure unit in accordance with the procedures contained in Section 4 of the appropriate Modification Summary 2 7 6 3 Return to service Verify that the unit power up self test sequence is successfully completed and no failure messages are annunciated NOTE There are no special handling requirements for the GNS 530W and GNS 430W 2 7 7 GA35 Antenna 2 7 7 1 Removal Gain access to antenna see General Arrangement Drawing for location Remove the sealant surrounding the antenna Remove the 4 screws that hold the antenna in place Disconnect the coaxial cable Py C2 IN 2 7 7 2 Installation To reinstall the GA 35 antenna 1 Clean the antenna doubler and aircraft skin of any e
39. page group When the cursor is ON the large MFD knob moves the cursor to highlight available fields The G600 system starts in normal mode when power is applied to the LRUs After completing the self test the database confirmation page is displayed Invalid or expired databases are displayed in yellow Press ENT to proceed to normal mode Normal mode consists of a Primary Flight Display PFD on the left screen and a Multifunction Display MFD on the right screen The AHRS alignment should complete within one minute and attitude should be displayed on the PFD System alerts are accessible via an ALERTS softkey at the lower right of the MFD During normal system operation with all aircraft systems and avionics powered there should not be any red Xs or system alerts on the GDU 620 To enter into Configuration Mode for the G600 system verify that the GDU 620 is off and the Installer Unlock Card P N 010 00769 60 is installed in the bottom card slot of the GDU 620 Apply power to the GDU 620 while holding the ENT key Release the ENT key when INITIALIZING SYSTEM appears in the upper left corner of the display Refer to the appropriate Modification Summary Section 4 for further Configuration instructions 2 3 2 GNS 530W 430W GNS 530W The GNS 530W is powered by Avionics Bus 1 which is normally controlled by the Avionics Bus 1 master switch The GNS 530W also contains a power switch which is controlled by the COM volume rotary knob near t
40. pproved aircraft inspection programs Instructions for Continued Airworthiness G600 GNS 530W GNS 430W GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B 190 01080 05 Rev 2 Page 11 of 29 2 5 1 GTX 330D Regulatory Testing With the transponders operating in normal mode the following regulatory tests are required to be performed e Altitude Reporting Equipment Tests in accordance with 14 CFR Part 91 411 and Part 43 Appendix E e ATC Transponder Tests and Inspections in accordance with 14 CFR Part 91 413 and Part 43 Appendix F These regulatory tests require the use of a Mode S transponder ramp tester Specific instructions for operating the ramp tester are contained in the applicable operator s manual Diversity Isolation Testing To satisfy the requirement for Part 43 Appendix F subparagraph e transponder diversity isolation must be verified To successfully test diversity isolation the installer must take the following action 1 Remove power from the ADC GNS 530W and GNS 430W for the duration of the diversity isolation test Cycle power to the GTX 330D and enter configuration mode On the ADS B TX Page select Pilot Set for ADS B TX Cycle power to the GTX 330D and allow the unit to initialize normally Place the GTX 330D in ground operating mode by pressing and holding the STBY key until the operating mode changes to GND At this point the technician should confirm the transponder s Mode S airborne
41. pressor Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 3 of 29 2 Instructions for Continued Airworthiness 2 1 Introduction Content Scope Purpose and Arrangement This document identifies the Instructions for Continued Airworthiness for the Garmin G600 Garmin GNS 530W Garmin GNS 430W Garmin GA 35 GPS Antennas Garmin GMA 347 Garmin GMX 200 WSI AV 200 Comant Cl 1530 1 WSI Antenna Garmin GTX 330D ES transponders and Comant Cl 105 Transponder Antennas installed in a Cessna 208 208B Caravan Definition of See Definitions in Section 1 2 Abbreviations Precautions None Units of measurement None STC SA02017SE D Maintenance Data or later revisions e 190 01080 02 General Arrangement G600 GNS430W GMA347 Cessna 208 208B Rev 5 e 190 01080 03 Modification Summary FX G600 GNS430W GMA347 Cessna 208 208B Rev 5 Sections 4 5 and Appendix A e 190 01080 04 Modification Summary FE G600 GNS430W GMA347 Cessna 208 208B Rev 6 Sections 4 5 and Appendix A e 190 01080 00 Install Dwg 150 G600 GNS430W GMA347 Cessna 208 208B Rev 6 e 190 01080 01 nstall Dwg 250 G600 GNS430W GMA347 Cessna 208 208B Rev 7 e 005 W0027 00 Installation Wiring FE G600 GNS430W GMA347 Cessna 208 208B Rev 9 e 005 W0027 04 Installation Wiring FX G600 GNS430W GMA347 Cessna 208 208B Rev 7 STC SA01712SE D
42. r the highlighted cursor location The Large Outer Knob selects the page group When the cursor is ON the large knob moves the cursor to highlight available fields There are dedicated ENT CLR and MENU keys on the right side of the unit System messages are viewable by pressing the MSG key at the bottom of the unit The GNS starts in normal mode when power is applied to the unit and the power switch is on After completing the self test the database confirmation page is displayed Invalid or expired databases are displayed in yellow Press ENT to proceed to the INSTRUMENT PANEL SELF TEST page CDI HSI indications may be verified while this page is displayed Press ENT to continue to satellite acquisition After a GPS position has been acquired the unit will be ready for operation During normal system operation with all aircraft systems and avionics powered there should not be any system messages displayed To enter into Configuration Mode for the GNS GPS NAV COM unit verify the unit turned off Apply power to the GNS while holding the ENT key Release the ENT key when INITIALIZING SYSTEM appears in the upper left corner of the display Refer to the appropriate Modification Summary Section 4 for further Configuration instructions 2 3 3 GMA 347 The GMA 347 is powered by Avionics Bus 2 which is normally controlled by the Avionics Bus 2 master switch The GMA 347 also contains a power switch which is controlled by the Pilot s volume
43. remove any RTV sealant which surrounds the base of the antenna 4 Carefully lower the antenna straight down only enough to gain access to the coaxial cable BNC connection Twist the BNC connector CCW to disconnect the cable Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 21 of 29 5 Remove the antenna from the aircraft Inspect the installation location including ground plane BNC connector coaxial cable and fasteners for corrosion or any other form of damage Repair any damage before proceeding in accordance with the Cessna Caravan Maintenance Manual D2078 21 13 and or the installation drawings listed in section 2 1 as applicable to service 2 7 14 Transponder DME Cable Reinstall the antenna in accordance with the Antenna Installation Drawing 005 00521 11 Perform the regulatory transponder testing required in section 2 5 1 prior to returning the aircraft Assembly Removal amp Replacement If a transponder or DME cable becomes damaged performs poorly or is beyond serviceable condition the entire cable assembly must be numbers and vendor information cable assemblies replaced Refer to Table 2 2 and Table 2 3 for cable assembly part Refer to Appendix A for instructions on servicing the transponder DME For transponder coaxial cables install the cables following the requirements of the Antenna Installation Drawin
44. rotary knob near the left side of the unit An AUD MKR circuit breaker on Avionics Bus 2 supplies power to the GMA 347 The GMA 347 is self contained with front panel controls Audio source selection is controlled by the top row of buttons with green LEDs indicating selected sources COM MIC selection buttons are on the bottom row with a green LED indicating the selected COM MIC The left dual concentric knob controls pilot intercom volume and squelch The right dual concentric knob controls copilot intercom volume and squelch The GMA 347 starts in normal mode when power is applied to the unit and the power switch is on All lights will momentarily illuminate during the power on self test Follow these steps to enter the GMA 347 Audio Panel into Configuration Mode 1 Ensure the GMA 347 is powered off 2 Locate connector PG11 which breaks out near connector PA28 underneath the pilot instrument panel above the rudder pedals 3 Plug 3 pin connector from GMA347 programming cable into PG11 plug other end into your computer serial port Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 8 of 29 4 Start the GMA Configuration tool GMA_CONFIG EXE Garmin P N 006 A01 15 00 on your computer 5 Power up the GMA 347 Refer to the appropriate Modification Summary Section 4 for further Configuration instructions 2 3 4 GMX 200 and WSI AV 200 To
45. s G600 GNS 530W GNS 430W GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B 190 01080 05 Rev 2 Page 10 of 29 Item Description Procedure Interval Perform an electrical bonding test for each listed LRU 1 Gain access to the LRU see General Arrangement Drawing for LRU location 2 Disconnect all harness antenna connectors from the LRU 3 Measure the resistance between the LRU and a nearby GDU 620 exposed portion of aircraft metallic structure GRS 77 f a For the GDU 620 verify the resistance is less than or equal to 40 milliohms GDC 74A s Every 2000 GMU 44 b eee ee ae resistance is less than flight hours or GTP 59 q np ten 10 years c For the remaining LRUs verify the resistance is GAD 43 ans whichever is less than or equal to 20 millionms GNS 530W ee first d Ifthe resistance is higher than values listed GNS 430W LRU cl bondino interf GMA 347 above remove clean bonding interfaces reinstall and re measure until half the resistance listed above or less is reached 4 Reconnect all disconnected harness antenna connectors and ensure they are secure Repeat for each listed LRU An electrical bonding test must be performed on the GA 35 Antennas For first GA 35 Antenna 1 Gain access to the antenna see General Arrangement Drawing for location 2 Disconnect the coaxial cable from the antenna connector Every 2000 3 Measure the resistance between the antenna base fli ef or
46. s Uk anys acolo SE oid bus Cet on EE E gu Syed ub es 17 PID OGADA oe soph ccna et clot Spe aA le Bad odo S TA eS is iBT St as oem 18 2 7 6 GNS 530W 430W GPS NAV COM ccc cpiensgessydasctaosnbasisdywcsy Sconces aeoanearphenianspcca yess vadouate revo 18 Skl SAPS SOPMMCN I errn it cokes ices E ES Weve REAA tock oda eves i cea voice E 19 2 1 8 GMA S47 A dio Panel esie e venta aruda iene asa EA E T tO RS 19 2 19 GMX 200o sac sahctong eis um Sud si creatine E vk ssc wal EEE give omnes as Sun Oa 20 2 7 10 WSI AV 200 and WSI Antenna ai scsscsceesysicex costed ecstura wt teleosanoaphiagh Senda bsnesivs av enlee apt 20 2 7 11 TAS SOD A shedhoes igahenss decades lacwetanatebbeines 20 2 7 12 Top Transponder Antenna Removal amp Replacement cccccesseeseceeseteeseneeeeeeees 21 2 7 13 Bottom Transponder Antenna Removal amp Replacement ccecceeseeeseeeteeeeees 21 2 7 14 Transponder DME Cable Assembly Removal amp Replacement cceeeeee 22 2 8 BIETE TEE In IE EE ease cept ATE AIA 23 2 9 Special Inspection Requirements eesesesesesesesseseseseseseseetssesrsrsesesesesesssseseseseseseseeeeesesese 23 2 9 1 Post Lightning Strike Inspection seesesssssesesesessssssesesesesesesessssesesesesestnterersesesesesesesesses 23 2 9 2 Special Inspection Techniques ssssesssssesesesessessesesesesesesessssrsssestsestsirtrersesesesesesesessns 23 2 10 Application of Protective Treatments cc ceesseseseseesessescecese
47. s follows a Start XPDR 1 in configuration mode hold the OFF key to power down the unit then hold the FUNC key and press the ON key b Press the FUNC key until the SQUAT SWITCH page is displayed Then use the CRSR and 8 9 keys to change the setting to NO Press the CRSR key until no fields are highlighted to save the changes Restart XPDR 1 in normal operating mode and select ALT mode Using the transponder test set verify XPDR 1 is in the on ground state This may be accomplished by one of the following methods a Verifying the length or width ADS B Out parameter is being transmitted or b Verifying the Mode S air ground status is on ground Select XPDR 2 using the transponder selector switch Apply power to the GNS 430W by resetting the NAV 2 circuit breaker Remove power from the GNS 530W by pulling the NAV 1 circuit breaker Ensure the GNS 430W is operating normally and has acquired a GPS position Repeat steps 6 though 11 on XPDR 2 Note references to XPDR 1 in these steps now refer to XPDR 2 The test is complete Reset the NAV 1 circuit breaker and select STBY mode on the transponder ypo o o o GTX 330D Installation Visual Inspection Conduct a visual inspection of the GTX 330D installation in the following locations 1 2 3 2 5 4 Inspect all GTX 330D knobs and buttons for legibility of labels and markings Inspect GTX 330D units for security of attachment Inspect mounting rack and hardware
48. seeeceeeeeseeseeeeaeeceseseeaeseenees 23 2 11 Data Relative to Structural Fasteners eeseecesessessesceceseseeececeeeseeececeeesceeeneeaeeceneneees 24 22 Special Tool S aut aa a mikou era aie POR ai nin aman atone intone 24 2 13 Additional Instructions ss siecle tnacoss cig aenvianamcenene monn au tonetinisos ouvir euneioeunamouses 24 PA COVSRAAGI IE SHO ch EEEE TT T A E E ee Aiea etalk es Basen 24 2 15 ICA Revision and Distribution ec eeccccsseseseescseeseeeesescesesecseseeseeecaeeeseescaeeaeseeseaeeaceeeaees 25 216 ASSISTANCE Asopos na e a N ec a AT N n A N 25 2 17 Implementation and Record Keeping ccccssessesesessessesceeeseseeeceeeseseeecesenssceeenceaeseenenseas 25 3 Airworthiness Hmla OS r rarr r aE teats e are A benuaues Soave apatuabe sta EEES venues 25 Appendix A Transponder DME Cable Connector Removal amp Replacement cece 26 A 1 Transponder Cable Connectors vis ssscictasiacensssseoensasacensspsnccvonshacsesbaneersssbacckhspeneskensnicdern tanec 26 A 2 DME able COnneGiOnsc mcscattcsstortncaes sestvaettect sansa it ches a a stander tetas 28 Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 2 of 29 1 Introduction 1 1 Purpose This document is designed for use by the installing agency as Instructions for Continued Airworthiness in response to 14 CFR 23 1529 and Part 23 Appendix G This ICA inclu
49. state is AIR by observing the ramp tester 6 Temporarily disable the ADS B Extended Squitter function on each GTX 330D by pressing the FUNC key until the ADS B TX page is displayed then toggle the ADS TX function off using the START STOP key 7 The diversity isolation test may now be conducted Note that it is critical to isolate the antenna under test from the antenna not being tested to achieve passing results of 220 dB isolation Use proper testing practices and follow the test equipment manufacturer s recommendations It is recommended that an antenna isolating device be utilized for this test 8 After completing tests on all four transponder antennas the ADC GNS 530W and GNS 430W may be powered back on and the ADS B TX function re enabled 9 If desired power cycle the GTX 330D and enter configuration mode On the ADS B TX Page select Enabled for the ADS B TX setting aR wh 2 5 2 GTX 330D ADS B Out Testing Perform the following procedure any time either GPS position source is replaced modified The test is performed using a transponder ramp test set such as the Aeroflex IFR 6000 or TIC TR 220 Note S W v5 30 or later is required on the TR 220 For instructions on operating the ramp tester refer to the manufacturer s documentation 1 Ensure the aircraft is in a location where a GPS signal can be received e g outdoors with a clear view of the sky 2 Power on the aircraft avionics and ensure that both transponders ar
50. this modification NOTE The Airworthiness Limitations section is FAA approved and specifies maintenance required under 43 16 and 91 403 of the Federal Aviation Regulations unless an alternative program has been FAA approved Paketan C E Soue QN 4 Michael Warren Date FAA APPROVED i a STC Unit Administrator ODA 240087 CE Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 25 of 29 The BNC connectors if damaged can be replaced individually as necessary without requiring complete cable assembly replacement A 1 Transponder Cable Connectors Table A 1 lists required tooling to accomplish the termination Table A 1 Transponder Cable Tooling Appendix A Transponder DME Cable Connector Removal amp Replacement Item Description Part No Hex Die Tooling Military P N M22520 5 35 Or Daniels P N Y137 Tool Frame M22520 5 01 HX4 Hex Size A Hex Solder Temperature 750 800F 1 Disconnect faulty connector from upper transponder antenna Cut the connector off completely using snips or diagonal cutters Make every attempt to limit the amount of cable which is removed along with the connector NOTE For proper transponder diversity performance all four cables must be within 12 inches total length of each other 2 Slide on heat shrink labels black adhesive heat shrink and crimp t
51. tion must be reloaded into the GAD 43 Refer to Section 4 of the appropriate Modification Summary for GAD 43 Software Loading procedure Verify that the configuration settings are correct on the GAD 43 Configuration page NOTE Viewing the GAD 43 configuration page on the GDU 620 causes the configuration values GAD 43 configuration to be written to the GAD 43 2 7 5 3 Return to Service After removing and reinstalling the GAD 48 the following return to service checks should be performed 1 Power up the G600 system with the GDU 620 in configuration mode 2 Conduct the GAD 43 Adapter Attitude Check in Section 5 of the appropriate Modification Summary 3 Restart the G600 system with the GDU 620 in normal mode 4 After valid attitude information is displayed on the GDU verify that there are no GAD alerts in the alerts window If alerts are present troubleshoot using Appendix A of the appropriate Modification Summary 5 Engage the autopilot and verify that the servos are active 6 Press the AP TEST soft key on the PFD Verify that the autopilot disconnects and the servos disengage 2 7 6 GNS 530W 430W GPS NAV COM 2 7 6 1 Removal To remove the GNS 530W or GNS 430W unit from the mounting rack insert a 3 32 inch hex drive tool into the access hole at the bottom of the unit face Rotate the hex tool counterclockwise until the unit is forced out about 3 8 inches and can be freely pulled from the rack 2 7 6 2 Installation The GNS 530W
52. ube Installer is responsible for remaking cable labels Use existing cable label as a reference 3 Strip the cable insulation according to the following diagram 0 925 23 50nn 0 420 0 300 0 00nn 7 62nn a a NOTE Take care not to nick the center conductor or shield braid Do not remove inner foil shield from dielectric 4 Install cable insulator onto center conductor butting it up against cable dielectric as shown CABLE INSULATOR Termination Instructions 90 Connectors Ref Emteq Dwg ES 105 5 Instructions for Continued Airworthiness G600 GNS 530W GNS 430W 190 01080 05 Rev 2 GMA 347 GTX 330D GMX 200 WSI AV 200 Cessna 208 208B Page 26 of 29 5 Tin the center conductor Flair the outer shield braid by gently rotating the center conductor and dielectric then finish to flare out taking care not disturbing the inner foil shield Do not remove the inner foil shield from the dielectric 6 Insert the cable into the rear of the connector body The inner foil shield goes inside the connector body and the braid shield goes outside the connector body with the center conductor going directly into the contact slot until the cable insulator buts against the contact ACCESS CAP SOFT SOLDER 7 Solder the center conductor to the contact Do not exceed specified solder temperatures in Table A 1 8 Slide the crimp tube over the braid up
53. xisting sealant or other material to ensure adequate bonding 2 Replace the o ring MS28775 116 between the fuselage skin and antenna 3 Secure the antenna using the 4 8 32 screws and torque to 12 15 inch pounds 4 Verify the resistance between the antenna and the aircraft metallic structure that forms the ground plane is equal to or less than 2 5 millionms per mating surface 5 Using sealing compound AMS S 8802 run a bead of sealant along the antenna where it meets the aircraft skin Ensure the antenna connectors do not become contaminated with sealant 6 Reconnect the coaxial cable to the antenna connector and ensure it is secure 2 7 7 3 Return to service Verify proper operation by successful completion of the self test of the interfaced GNS 530W or 430W NOTE There are no special handling requirements for the GA 35 2 7 8 GMA 347 Audio Panel 2 7 8 1 Removal To remove the unit from the rack turn the hex wrench counterclockwise until it disengages from the rack 2 7 8 2 Installation The GMA 347 unit is installed in the rack by sliding it straight in until it stops about 1 inch short of the final position Insert the hex drive tool into the access hole at the bottom of the unit face Rotate the hex tool clockwise while pressing on the bezel until the unit is firmly seated in the rack Original GMA 347 is reinstalled No configuration is required Replacement or repaired GMA 347 is installed Instructions for Continued

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