Garmin Part 23 Aml Stc Sa01933La D Instruction Manual APPENDIX A

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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

Record of Revision

Rev.

Date

Description of Change

1

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.

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

TABLE OF CONTENTS

1. Introduction .......................................................................................................................................... 3

1.1 Purpose ...................................................................................................................................... 3

1.2 Definitions .................................................................................................................................. 3

2. Instructions for Continued Airworthiness ........................................................................................ 4

2.1 Introduction ................................................................................................................................ 4

2.2 Description of Alteration ........................................................................................................... 5

2.3 Control/Operation Information................................................................................................. 7

2.3.1 G600 System ......................................................................................................................... 7

2.3.2 GNS 530W/430W ................................................................................................................. 7

2.3.3 GMA 347 ................................................................................................................................ 8

2.3.4 GMX 200 and WSI AV-200 ................................................................................................. 9

2.3.5 GTX 330D .............................................................................................................................. 9

2.4 Servicing Information .............................................................................................................. 10

2.5 Periodic Maintenance Instructions ....................................................................................... 10

2.5.1 GTX 330D Regulatory Testing ......................................................................................... 12

2.5.2 GTX 330D ADS-B Out Testing ......................................................................................... 12

2.5.3 GTX 330D Installation Visual Inspection ........................................................................ 13

2.5.4 GTX 330D Installation Electrical Bonding Test .............................................................. 13

2.6 Troubleshooting Information ................................................................................................. 14

2.7 Removal and Installation Information .................................................................................. 14

2.7.1 GDU 620 .............................................................................................................................. 14

2.7.2 GRS 77................................................................................................................................. 15

2.7.3 GMU 44 ................................................................................................................................ 16

2.7.4 GDC 74A .............................................................................................................................. 17

2.7.5 GAD 43................................................................................................................................. 18

2.7.6 GNS 530W/430W GPS/NAV/COM .................................................................................. 18

2.7.7 GA 35 Antenna ................................................................................................................... 19

2.7.8 GMA 347 Audio Panel ....................................................................................................... 19

2.7.9 GMX 200 .............................................................................................................................. 20

2.7.10 WSI AV-200 and WSI Antenna .................................................................................... 20

2.7.11 GTX 330D........................................................................................................................ 20

2.7.12 Top Transponder Antenna Removal & Replacement ............................................... 21

2.7.13 Bottom Transponder Antenna Removal & Replacement ......................................... 21

2.7.14 Transponder/DME Cable Assembly Removal & Replacement ............................... 22

2.8 Diagrams .................................................................................................................................. 23

2.9 Special Inspection Requirements ......................................................................................... 23

2.9.1 Post-Lightning Strike Inspection ....................................................................................... 23

2.9.2 Special Inspection Techniques ......................................................................................... 23

2.10 Application of Protective Treatments ................................................................................... 23

2.11 Data Relative to Structural Fasteners .................................................................................. 24

2.12 Special Tools ........................................................................................................................... 24

2.13 Additional Instructions ............................................................................................................ 24

2.14 Overhaul Period ...................................................................................................................... 24

2.15 ICA Revision and Distribution ............................................................................................... 25

2.16 Assistance ................................................................................................................................ 25

2.17 Implementation and Record Keeping .................................................................................. 25

3. Airworthiness Limitations ................................................................................................................ 25

Appendix A. Transponder/DME Cable Connector Removal & Replacement .............................. 26

A.1 Transponder Cable Connectors ........................................................................................... 26

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 3 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 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

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 CI 1530-1 WSI Antenna.

SA01512WI-D Installation of dual GTX 330D ES transponders and CI 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 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 4 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 CI 1530-

1 WSI Antenna, Garmin GTX 330D ES transponders, and Comant CI 105

Transponder Antennas installed in a Cessna 208/208B Caravan.

Definition of

Abbreviations:

See Definitions in Section 1.2

Precautions:

None

Units of measurement:

None

STC SA02017SE-D

Maintenance Data

(or later revisions)

• 190-01080-02, General Arrangement, G600 GNS430W GMA347 Cessna

208/208B, Rev. 5

• 190-01080-03, Modification Summary FX, G600 GNS430W GMA347 Cessna

208/208B, Rev. 5 (Sections 4, 5, and Appendix A)

• 190-01080-04, Modification Summary FE, G600 GNS430W GMA347 Cessna

208/208B, Rev. 6 (Sections 4, 5, and Appendix A)

• 190-01080-00, Install Dwg 150, G600 GNS430W GMA347 Cessna

208/208B, Rev. 6

• 190-01080-01, Install Dwg 250, G600 GNS430W GMA347 Cessna

208/208B, Rev. 7

• 005-W0027-00, Installation Wiring FE, G600 GNS430W GMA347 Cessna

208/208B, Rev. 9

• 005-W0027-04, Installation Wiring FX, G600 GNS430W GMA347 Cessna

208/208B, Rev. 7

STC SA01712SE-D

Maintenance Data

(or later revisions)

• 005-00368-12, Avionics Installation, GNS 530(W), GMX200, WSI AV-200,

150, Rev 8

• 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)

• 005-00521-11, GTX330D Antenna Installation in Cessna 208/208B, Rev. 5

• 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

Retention:

This document, or the information contained within, will be included in the

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 5 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.

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 6 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 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 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 7 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 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 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 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 8 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 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 9 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 10 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 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.

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

GRS 77 AHRS

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

indicating the model has expired. The model can be updated by

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.

On condition

GDC 74A ADC

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.

The tests of Part 43 Appendix E sub-paragraphs (iv)

(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.

24 Calendar

Months

GA 35 GPS

Antennas,

CI 1530-1 WSI

Antenna

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

that all sealing fillets around the antennas are in good condition.

If the antenna is broken, cracked, or dented it must be replaced.

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).

12 Calendar

Months [1]

GDU 620,

GRS 77,

GDC 74A,

GMU 44,

GTP 59,

GAD 43,

GNS 530W,

GNS 430W,

GMA 347

Conduct a visual inspection (look for signs of wear, deterioration,

or damage to wires, backshells, or connectors) on units and their

wire harnesses to ensure installation integrity:

1. Gain access to LRU (see General Arrangement Drawing

for LRU locations)

2. Inspect each unit for security of attachment.

3. Inspect all knobs and buttons for legibility.

4. Inspect condition of wiring, routing and

attachment/clamping.

5. Inspect integrity of shield terminations.

6. Inspect for signs of corrosion on equipment and rack

installations.

12 Calendar

Months [1]

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 11 of 29

Item Description/Procedure Interval

GDU 620,

GRS 77,

GDC 74A,

GMU 44,

GTP 59,

GAD 43,

GNS 530W

GNS 430W,

GMA 347

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. For the GTP 59, verify the resistance is less than

or equal to 5 milliohms

c. For the remaining LRUs, verify the resistance is

less than or equal to 20 milliohms

d. If the resistance is higher than values listed

above, remove LRU, 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.

Every 2000

flight hours or

ten (10) years,

whichever is

first

GA 35 GPS

Antennas

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.

3. Measure the resistance between the antenna base

connector and a nearby exposed portion of aircraft

structure (example: exposed rivet on fuselage stringer).

4. Verify the resistance is equal to or less than 5 milliohms.

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.

Every 2000

flight hours or

ten (10) years,

whichever is

first

GTX 330D

Regulatory Testing

The GTX 330D transponders must be tested and shown to

comply with 14 CFR Part 91.411, 91.413 and Part 43 Appendix E

and F as described in section 2.5.1.

24 Calendar

Months

GTX 330D

ADS-B Out Testing

The GTX 330D transponders must be shown to comply with 14

CFR Part 91.227 as described in section 2.5.2.

Replacement of

GNS 530W or

GNS 430W

GTX 330D, and

CI 105 Antennas

A visual inspection of the GTX 330D transponders and CI 105

antennas must be performed as described in section 2.5.3. 12 Calendar

Months [1]

GTX 330D, and

CI 105 Antennas

An electrical bonding test of the GTX 330D transponders and CI

105 antennas must be performed as described in section 2.5.4.

Every 2000

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 approved aircraft inspection programs.

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

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. 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.

2. Cycle power to the GTX 330D and enter configuration mode.

3. On the ADS-B TX Page, select Pilot Set for ADS-B TX.

4. Cycle power to the GTX 330D and allow the unit to initialize normally.

5. 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 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 ≥20 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.

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 are 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:

• 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 13 of 29

• 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

9. 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.” Press the CRSR key until no fields

are highlighted to save the changes.

10. Restart XPDR 1 in normal operating mode and select ALT mode.

11. 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.”

12. Select XPDR 2 using the transponder selector switch.

13. 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.

14. Repeat steps 6 though 11 on XPDR 2. Note: references to XPDR 1 in these steps now refer to

XPDR 2.

15. The test is complete. Reset the NAV 1 circuit breaker and select STBY mode on the transponder

2.5.3 GTX 330D Installation Visual Inspection

Conduct a visual inspection of the GTX 330D installation in the following locations:

1. Inspect all GTX 330D knobs and buttons for legibility of labels and markings.

2. Inspect GTX 330D units for security of attachment.

3. Inspect mounting rack and hardware for integrity.

a. Verify the racks, fasteners, and support structure are in good condition and are securely

fastened.

4. 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.

5. 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.

6. 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.

7. 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 cracking or corrosion at the installation site.

2.5.4 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 milliohms 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 14 of 29

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. 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 milliohms.

4. Reinstall the 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 Isocryl 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 milliohms.

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 sides.

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 15 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

“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 620 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 connector 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 16 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 present. If alerts are present, troubleshoot using Appendix A

of the appropriate Modification Summary.

Table 2-1. GRS 77 Calibration Criteria

Condition

Calibrations Required

GRS 77

Pitch/Roll

Offset

See Section 4 of

Modification

Summary

GRS/GMU

Magnetic

Calibration

See Section 4 of

Modification

Summary

Engine Run-up

Vibration

Test

See Section 4 of

Modification

Summary

GRS 77 AHRS was removed and/or

replaced. The mounting tray was NOT

removed and the mounting tray bolts

were NOT loosened.

None Required.

GRS 77 AHRS was removed and/or

replaced. The mounting tray WAS

removed and/or mounting tray bolts

WERE loosened.

X

X

X

GRS 77 AHRS Configuration Module

was replaced.

X X X

2.7.3 GMU 44

2.7.3.1 Removal

1. Gain access to the GMU 44 magnetometer (see General Arrangement Drawing for location).

2. Unscrew the three screws that hold the GMU 44 to its mounting rack.

3. Carefully lift the GMU 44 from the rack.

4. Disconnect the wiring harness.

2.7.3.2 Installation

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 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 17 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. Disconnect 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.

2.7.4.2 Installation

1. Place the unit in the mounting tray.

2. Position the locking clamp and fasten using the thumbscrews.

3. Connect the pitot/static plumbing.

4. Inspect the connector and pins for damage. Repair any damage.

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 within 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 18 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 configuration 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 43, 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 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 19 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 GA 35 Antenna

2.7.7.1 Removal

1. Gain access to antenna (see General Arrangement Drawing for location)

2. Remove the sealant surrounding the antenna

3. Remove the 4 screws that hold the antenna in place

4. Disconnect the coaxial cable.

2.7.7.2 Installation

To reinstall the GA 35 antenna:

1. Clean the antenna, doubler, and aircraft skin of any existing 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 milliohms 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 Airworthiness G600, GNS 530W, GNS 430W, 190-01080-05 Rev. 2

GMA 347, GTX 330D, GMX 200, WSI AV-200 Cessna 208/208B Page 20 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 configuration 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 3/32” 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 208/208B Page 21 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:

• 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

• Complete all software verification and configuration procedures in accordance with Section 4 of

the appropriate Modification Summary.

• Perform the GTX Regulatory Testing specified in section 2.5.1.

2.7.12 Top Transponder Antenna Removal & 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 this 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. On the 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 & 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 Isocryl

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 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 22 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.

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.

2.7.14 Transponder/DME Cable Assembly Removal & Replacement

If a transponder or DME cable becomes damaged, performs poorly, or is beyond serviceable condition,

the entire cable assembly must be replaced. Refer to Table 2-2 and Table 2-3 for cable assembly part

numbers and vendor information. Refer to Appendix A for instructions on servicing the transponder/DME

cable assemblies.

For transponder coaxial cables, install the cables following the requirements of the Antenna Installation

Drawing, 005-00521-11.

Table 2-2. Transponder Coaxial Cable Information

Item

Description / Part No.

Manufacturer

Emteq

5349 S. Emmer Drive

New Berlin, WI 53151

(888) 679-6170

PMA Approved Cable

Assemblies P/Ns

BR19252BS-301 (Coax Cable Assy, XPDR1 – Top)

BR19252BS-501 (Coax Cable Assy, XPDR2 – Top)

BS19252BS-401 (Coax Cable Assy, XPDR1 – Bottom)

BS19252BS-601 (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:

50 Ohm

Attenuation

6.11 dB/100 ft @ 1090 MHz

Right Angle Connector P/N

Emteq BMR340-1

Straight Connector P/N

Emteq BMS340-1

Adhesive Heat Shrink

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

Assembly P/N

BS31277BS-DME1

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 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

2.8 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.

2.9.1.1 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 GA 35 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 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 24 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.

Location

(see General

Arrangement

Drawing)

FASTENER TYPE AND TORQUE

6-32 Screw

12-15 inch-

pounds

8-32 Screw

12-15 inch-

pounds

8-32 Nut

12-15 inch-

pounds

10-32 Screw

22-25 inch-

pounds

NUT, 5/16",

HEX, SKIRT

100 inch-

pounds

Instrument Panel,

Instruments, and

Avionics Stack X X

GRS 77 X

GDC 74A X X

GAD 43 X

GA 35 X

GMU 44 X X

GTP 59 X

Transponder

Antennas X

DME Antenna X

WSI Antenna X

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:

• 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 26 of 29

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.

Table A-1. Transponder Cable Tooling

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

Termination Instructions, 90° Connectors (Ref Emteq Dwg ES-105-5):

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 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:

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:

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

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.

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 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:

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 28 of 29

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 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 29 of 29

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. 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 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.