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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. 151st Street
Olathe, Kansas 66062 USA
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Record of Revision |
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Rev. |
Date |
Description of Change |
1 |
01/25/10 |
Initial Release |
2 |
05/21/14 |
Added maintenance data from prerequisite installations and updated |
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maintenance data for the G600, GNS 430W/530W, GMX 200, GMA 347, |
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and GTX 330D Transponders. |
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TABLE OF CONTENTS |
3 |
1. |
Introduction.......................................................................................................................................... |
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1.1 |
Purpose ...................................................................................................................................... |
3 |
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1.2 |
Definitions .................................................................................................................................. |
3 |
2. |
Instructions for Continued Airworthiness........................................................................................ |
4 |
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2.1 |
Introduction ................................................................................................................................ |
4 |
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2.2 |
Description of Alteration........................................................................................................... |
5 |
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2.3 |
Control/Operation Information................................................................................................. |
7 |
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2.3.1 |
G600 System......................................................................................................................... |
7 |
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2.3.2 |
GNS 530W/430W ................................................................................................................. |
7 |
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2.3.3 |
GMA 347................................................................................................................................ |
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2.3.4 GMX 200 and WSI AV-200 ................................................................................................. |
9 |
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2.3.5 |
GTX 330D.............................................................................................................................. |
9 |
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2.4 |
Servicing Information.............................................................................................................. |
10 |
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2.5 |
Periodic Maintenance Instructions ....................................................................................... |
10 |
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2.5.1 |
GTX 330D Regulatory Testing ......................................................................................... |
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2.5.2 GTX 330D ADS-B Out Testing......................................................................................... |
12 |
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2.5.3 GTX 330D Installation Visual Inspection ........................................................................ |
13 |
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2.5.4 GTX 330D Installation Electrical Bonding Test.............................................................. |
13 |
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2.6 |
Troubleshooting Information ................................................................................................. |
14 |
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2.7 |
Removal and Installation Information .................................................................................. |
14 |
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2.7.1 |
GDU 620 .............................................................................................................................. |
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2.7.2 |
GRS 77................................................................................................................................. |
15 |
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2.7.3 |
GMU 44................................................................................................................................ |
16 |
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2.7.4 |
GDC 74A.............................................................................................................................. |
17 |
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2.7.5 |
GAD 43................................................................................................................................. |
18 |
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2.7.6 |
GNS 530W/430W GPS/NAV/COM.................................................................................. |
18 |
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2.7.7 |
GA 35 Antenna ................................................................................................................... |
19 |
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2.7.8 GMA 347 Audio Panel ....................................................................................................... |
19 |
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2.7.9 |
GMX 200.............................................................................................................................. |
20 |
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2.7.10 WSI AV-200 and WSI Antenna .................................................................................... |
20 |
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2.7.11 GTX 330D........................................................................................................................ |
20 |
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2.7.12 Top Transponder Antenna Removal & Replacement............................................... |
21 |
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2.7.13 Bottom Transponder Antenna Removal & Replacement......................................... |
21 |
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2.7.14 Transponder/DME Cable Assembly Removal & Replacement............................... |
22 |
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2.8 |
Diagrams.................................................................................................................................. |
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2.9 |
Special Inspection Requirements......................................................................................... |
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2.9.1 |
Post-Lightning Strike Inspection....................................................................................... |
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2.9.2 |
Special Inspection Techniques......................................................................................... |
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2.10 |
Application of Protective Treatments................................................................................... |
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2.11 |
Data Relative to Structural Fasteners.................................................................................. |
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2.12 |
Special Tools ........................................................................................................................... |
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2.13 |
Additional Instructions............................................................................................................ |
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2.14 |
Overhaul Period ...................................................................................................................... |
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2.15 |
ICA Revision and Distribution ............................................................................................... |
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2.16 |
Assistance................................................................................................................................ |
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2.17 |
Implementation and Record Keeping .................................................................................. |
25 |
3. |
Airworthiness Limitations ................................................................................................................ |
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Appendix A. Transponder/DME Cable Connector Removal & Replacement.............................. |
26 |
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A.1 |
Transponder Cable Connectors ........................................................................................... |
26 |
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A.2 |
DME Cable Connectors ......................................................................................................... |
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
1.1Purpose
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 includes 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 CI 1530-1 WSI Antenna, Garmin GTX 330D ES transponders, and Comant CI 105 Transponder Antennas when installed under the following STCs.
STC Number |
Description |
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SA02017SE-D |
Installation of the G600, GNS 430W, GA 35 GPS Antenna, and GMA 347. |
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(Requires installation of SA01712SE-D and SA01512WI-D as prerequisites) |
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SA01712SE-D |
Installation of the GNS 530W, GA 35 GPS Antenna, GMX 200, WSI AV-200, |
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and CI 1530-1 WSI Antenna. |
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SA01512WI-D |
Installation of dual GTX 330D ES transponders and CI 105 Transponder |
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Antennas. |
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1.2Definitions
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 Suppressor
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 |
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Content, Scope, |
This document identifies the Instructions for Continued Airworthiness for the |
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Purpose and |
Garmin G600, Garmin GNS 530W, Garmin GNS 430W, Garmin GA 35 GPS |
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Arrangement: |
Antennas, Garmin GMA 347, Garmin GMX 200, WSI AV-200, Comant CI 1530- |
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1 WSI Antenna, Garmin GTX 330D ES transponders, and Comant CI 105 |
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Transponder Antennas installed in a Cessna 208/208B Caravan. |
Definition of |
See Definitions in Section 1.2 |
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Abbreviations: |
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Precautions: |
None |
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Units of measurement: |
None |
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STC SA02017SE-D |
• 190-01080-02, General Arrangement, G600 GNS430W GMA347 Cessna |
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Maintenance Data |
208/208B, Rev. 5 |
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(or later revisions) |
• 190-01080-03, Modification Summary FX, G600 GNS430W GMA347 Cessna |
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208/208B, Rev. 5 (Sections 4, 5, and Appendix A) |
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• 190-01080-04, Modification Summary FE, G600 GNS430W GMA347 Cessna |
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208/208B, Rev. 6 (Sections 4, 5, and Appendix A) |
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• 190-01080-00, Install Dwg 150, G600 GNS430W GMA347 Cessna |
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208/208B, Rev. 6 |
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• 190-01080-01, Install Dwg 250, G600 GNS430W GMA347 Cessna |
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208/208B, Rev. 7 |
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• 005-W0027-00, Installation Wiring FE, G600 GNS430W GMA347 Cessna |
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208/208B, Rev. 9 |
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• 005-W0027-04, Installation Wiring FX, G600 GNS430W GMA347 Cessna |
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208/208B, Rev. 7 |
STC SA01712SE-D |
• 005-00368-12, Avionics Installation, GNS 530(W), GMX200, WSI AV-200, |
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Maintenance Data |
150, Rev 8 |
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(or later revisions) |
• 005-00368-13, Avionics Installation, GNS 530(W), GMX200, WSI AV-200, |
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250, Rev 9 |
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• 190-00607-04, GMX 200 Installation Manual, Rev. B |
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• WSI 305427-00, WSI AV100/AV-200 Installation Manual |
STC SA01512WI-D |
• 005-00521-11, GTX330D Antenna Installation in Cessna 208/208B, Rev. 5 |
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Maintenance Data |
• 005-00521-13, DME Antenna Reassignment, Cessna 208/208B, Rev. 6 |
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(or later revisions) |
• 005-00521-14, Avionics Bus 1 Switch/Breaker Modification, Cessna |
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208/208B, Rev. 2 |
Retention: |
This document, or the information contained within, will be included in the |
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aircraft’s permanent records. |
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 4 of 29 |
2.2Description 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. 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. 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 CI 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 CI 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, latitude, 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 KFC150equipped 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 CI105s 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 |
2.3Control/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. The following circuit breakers provide power to the individual LRUs:
•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 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 selftest, 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 the 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 dualconcentric 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 for 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 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-A0115-00), on your computer.
5.Power up the GMA 347.
Refer to the appropriate Modification Summary, Section 4, for further Configuration instructions.
2.3.4 GMX 200 and WSI AV-200
To 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 |
Page 9 of 29 |
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