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 & ICA (from prerequisite STC SA01512WI-D) Garmin International, Inc. 1200 E.
TABLE OF CONTENTS 1. Introduction.......................................................................................................................................... 3 1.1 Purpose ...................................................................................................................................... 3 1.2 Definitions .................................................................................................................................. 3 2.
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.
2. Instructions for Continued Airworthiness 2.
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. Figure 1 - Equipment Locations (C208B as shown, C208 similar) 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.
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.
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 have individual power switches and are powered when the bus is energized and the circuit breakers are closed.
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 dualconcentric knobs. Pressing the knob toggles between COM and NAV frequency selection.
4. Start the GMA Configuration tool, GMA_CONFIG.EXE (Garmin P/N 006-A0115-00), on your computer. 5. Power up the GMA 347. Refer to the appropriate Modification Summary, Section 4, for further Configuration instructions. 2.3.
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 CI 105 Transponder Antennas, and Comant CI 1530-1 WSI Antenna are non-repairable; in the event of a failure, the antenna must be replaced.
Item GDU 620, GRS 77, GDC 74A, GMU 44, GTP 59, GAD 43, GNS 530W GNS 430W, GMA 347 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 exposed portion of aircraft metallic structure a. For the GDU 620, verify the resistance is less than or equal to 40 milliohms b.
2.5.1 GTX 330D Regulatory Testing With the transponders operating in normal mode, the following regulatory tests are required to be performed: • Altitude Reporting Equipment Tests in accordance with 14 CFR Part 91.411 and Part 43 Appendix 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.
9. 10. 11. 12. 13. 14. 15. • SDA value of 2 (≤ 1x10-5) • SIL value of 3 (≤ 1 x10-7) • NACp value of 8 or greater • NIC value of 7 or greater Reset the XPDR 1 squat switch configuration 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 “NO.
1. 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 milliohms. 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 milliohms. 4.
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.
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 recalibration 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.
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.
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. 2. 3. 4. Gain access to the GAD 43 (see General Arrangement Drawing for location) Disconnect the GAD 43 connector. Remove the six mounting screws. 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.
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.
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. 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.
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.
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 CI 105 transponder antennas, DME antenna, and their associated installation shall be inspected. 2.9.1.
2.11 Data Relative to Structural Fasteners Refer to the following table for data on the location, type, and torque values for structural fasteners.
Appendix A. Transponder/DME Cable Connector Removal & Replacement 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. Item Hex Die Tooling Tool Frame Hex Size Solder Temperature Table A-1. Transponder Cable Tooling Description / Part No.
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.
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.
4. Install cable insulator onto center conductor butting it up against cable dielectric, as shown: 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.
