CHAPTER 23 - Communications - Discovery Aviation€¦ · CHAPTER 23 COMMUNICATIONS . COMMUNICATIONS XL-2 AIRPLANE Chapter 23 P/N 135A-970-100 ... with Jeppesen database …

COMMUNICATIONS XL-2 AIRPLANE

P/N 135A-970-100 Chapter 23 REVISION D Page 1 of 42

CHAPTER 23

COMMUNICATIONS


Chapter 23 P/N 135A-970-100 Page 2 of 42 REVISION D

Copyright © 2010 All rights reserved. The information contained herein is proprietary to Liberty Aerospace, Incorporated. It is prohibited to reproduce or transmit in any form or by any means, electronic or mechanical, including photocopying, recording, or use of any information storage and retrieval system, any portion of this document without express written permission of Liberty Aerospace Incorporated.


P/N 135A-970-100 Chapter 23 REVISION D Page 3 of 42

Table of Contents

SECTION 23-00 GENERAL 5 SECTION 23-10 SPEECH COMMUNICATIONS 9

SECTION 10-01 GARMIN GNS430 COM/NAV/GPS 9 SECTION 10-02 GARMIN GNS 530 COM/NAV/GPS 10 SECTION 10-03 GARMIN GNS 430W AND GNS 530W COM/NAV/GPS WAAS 11 SECTION 10-04 GARMIN SL30 COM/NAV RADIO 11 SECTION 10-05 GARMIN SL40 COM RADIO 12 SECTION 10-06 PUSH-TO-TALK CONTROL OF THE COMMUNICATIONS 12 SECTION 10-07 PERIODIC MAINTENANCE 12 SECTION 10-08 VHF TRANSCEIVER PROCEDURES 12

TRANSCEIVER REMOVAL 13 TRANSCEIVER INSTALLATION 14 AVIONICS PANEL REMOVAL 15 AVIONICS PANEL INSTALLATION 17 TRANSCEIVER OPERATION CHECK AND INSPECTION 18

SECTION 10-09 TROUBLESHOOTING GUIDE 19 SECTION 10-10 COM/NAV/GPS ANTENNA 19 SECTION 10-11 PERIODIC MAINTENANCE 20 SECTION 10-12 COM/NAV/GPS ANTENNA PROCEDURES 21

MODEL CI 2480-200 ANTENNA REMOVAL 22 MODEL CI 2480-200 ANTENNA INSTALLATION 25 MODEL CI 2580-200 ANTENNA REMOVAL 28 MODEL CI 2580-200 ANTENNA INSTALLATION 31 COM/NAV/GPS ANTENNA INSPECTION 34

SECTION 10-13 TROUBLESHOOTING GUIDE 36 SECTION 23-50 AUDIO INTEGRATION 37

SECTION 50-01 GMA 340 AUDIO/ICS SYSTEM 37 SECTION 50-02 AUDIO SYSTEM PROCEDURES 38

GMA 340 AUDIO PANEL REMOVAL 39 GMA 340 AUDIO PANEL INSTALLATION 40 GMA340 OPERATION CHECK AND INSPECTION 41

SECTION 50-03 TROUBLESHOOTING GUIDES 42


Chapter 23 P/N 135A-970-100 Page 4 of 42 REVISION D

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P/N 135A-970-100 23-00 REVISION ~ Page 5 of 42

Section 23-00 General The XL-2 has a Garmin VHF radio system, used for communication between the airplane and a ground station or between airplanes. The system operates in the frequency ranges of 118.000 to 136.975 MHz, and has 760 channels with a separation of 25 kHz. Up to two communications radios may be available for use depending on the avionics options package installed. Options packages are comprised of Garmin COM/NAV, COM/NAV/GPS and Audio Panel units of the following model types:

• GMA 340 Audio Panel • GNS 530 COM/NAV/GPS • GNS 430 COM/NAV/GPS • GNS 430W COM/NAV/GPS WAAS • GNS 530W COM/NAV/GPS WAAS • SL 30 COM/NAV • SL 40 COM

Table 23-1 shows the different option packages built from the units above; permit the installation of one of the following Garmin communication radio configurations. All of these options come with a GMA340 audio panel. See Figure 23-1 for a view of typical installations of the communication transceivers.

COM 1 Position COM 2 Position Model Description Model Description

GNS 530 (or W) COM/NAV/GPS GNS 530 (or W) COM/NAV/GPS GNS 430 (or W) COM/NAV/GPS GNS 530 (or W) COM/NAV/GPS SL30 COM/NAV GNS 530 (or W) COM/NAV/GPS SL40 COM/NAV GNS 430 (or W) COM/NAV/GPS GNS 430 (or W) COM/NAV/GPS GNS 430 (or W) COM/NAV/GPS GNS 430 (or W) COM/NAV/GPS SL30 COM/NAV GNS 430 (or W) COM/NAV/GPS SL40 COM SL30 COM/NAV SL30 COM/NAV SL30 COM/NAV SL30 COM/NAV SL40 COM SL40 COM

Table 23-1 Table Showing the Various Avionics Packages Available for the XL2 Airplane


23-00 P/N 135A-970-100 Page 6 of 42 REVISION ~

An avionics upgrade option is available to configurations listed above that replaces GNS 430 and GNS 530 COM/NAV/GPS units with GPS WAAS (Wide Area Augmentation System) capable GNS 430W and GNS 530W COM/NAV/GPS units. WAAS capable GNS units look identical to their Non-WAAS predecessors. Refer to the aircraft equipment list. This list has the information on the versions of the radios installed in the airplane. On power up of the GNS430/530 transceivers will display a screen similar (depending on model) to the screen shown in Figure 23-2. Verify the unit identification and software revisions from this display.

In addition to the communication radio stack fitted to the center instrument console, there are two antennas fitted in a forward and aft position as shown in Figure 23-3. The forward antenna is typically for the COM1 radio and the aft antenna for the COM2 radio for all radio installation options. Audio connections for the pilot and co-pilot are made by an overhead audio jack panel, see Figure 23-19, located center and aft of the seat backs. There is no cabin speaker installed in the airplane. Transmit switches (PTT) are located at the tip of the pilot and co-pilot control sticks.

Figure 23-1 Typical Radio Installation on the left, is the GNS530/430 typical installation, on the right, is the GNS 430W/SL30 typical installation

Figure 23-2 GNS Model and Software Verification

GNS Model Identifier GNS 430W or GNS 530W

• Main Software Revision

• GPS Software Revision • If not 3.0 or greater

perform Garmin Ltd. Software Service Bulletin 0740 Revision A, dated November 29, 2007



The alternator, and/or battery provide power for the avionics. The power goes through the Avionics Master switch and the COM circuit breaker. There is a dedicated circuit breaker for each radio. The size of circuit breaker matches the radio option installed.

Figure 23-3 Communications Equipment Placement

COM 1

COM 2



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P/N 135A-970-100 23-10 REVISION D Page 9 of 42

Section 23-10 Speech Communications On the Liberty Aerospace, Inc. XL-2 airplane, speech communications is by VHF transceivers mounted in the avionics panel. There can be several models of VHF transceiver(s) installed in the airplane. Unless otherwise ordered, airplanes come equipped with transceivers from Garmin. The models installed in the airplane may include the GNS 530, GNS 430, SL 30, SL 40, GNS 530W, and/or the GNS 430W transceiver.

Section 10-01 Garmin GNS430 COM/NAV/GPS The GNS 430 COM/NAV/GPS transceiver provides radio communication between pilot and ground stations, and VOR/LOC/GS/GPS reception. The installation of the GNS 430 transceiver can be in either the COM 1 or COM 2 stack position of the avionics panel depending on the radio option package installed.

The description of the NAV and GPS subsystem may be found in Liberty Maintenance Manual Chapter 34-Navigation and Pitot/Static.

The GNS 430 series units are 6.25 inch wide by 2.66 inch high. The display is a 128 by 240-pixel color LCD. The units include two removable data cards, one with a Jeppesen database, and the second an optional custom data card.

The display of the GNS 430 has a special anti-reflective coating, which is very sensitive to skin oils, waxes and abrasive cleaners. It is very important to clean the lens with a lint-free cloth using an eyeglass lens cleaner specified safe for antireflective coatings.

The GNS 430 GPS receiver is certified for IFR en route, terminal and non-precision approach operations. The VHF communications transceiver is an IFR certified airborne unit. VOR/Localizer and Glideslope receivers are also IFR certified.

Figure 23-4 GNS 430 Face Plate Key Slot


23-10 P/N 135A-970-100 Page 10 of 42 REVISION D

The Garmin user guide and installation manual for the GNS 430 COM/NAV/GPS receiver has additional information on the control functions and features.

Section 10-02 Garmin GNS 530 COM/NAV/GPS The GNS 530 COM/NAV/GPS transceiver provides radio communication between pilot and ground stations. This radio also provides VOR/LOC GS and GPS reception. The typically installation of the GNS 530 is in the COM 1 stack position of the avionics panel depending on the radio option package installed.

The description of the NAV and GPS subsystem is in Chapter 34.

The GNS 530 series units are 6.25 inch wide by 4.60 inch high. The display is a 234 by 320-pixel color LCD. The radio includes two removable data cards, one with a Jeppesen database, and the second an optional custom data card.

The display of the GNS 530 has a special anti-reflective coating, which is very sensitive to skin oils, waxes and abrasive cleaners. It is very important to clean the lens with a lint-free cloth using an eyeglass lens cleaner specified safe for antireflective coatings.

The VHF communications transceiver is an IFR certified airborne unit. The VOR/Localizer and Glideslope receivers are also IFR certified. The GNS 530 GPS receiver is IFR certified for en route, terminal, and non-precision approach operations.

Figure 23-5 GNS 530 Face Plate Key Slot



The Garmin user guide and installation manual for the GNS 530 COM/NAV/GPS receiver has additional information on the control functions and features.

Section 10-03 Garmin GNS 430W and GNS 530W COM/NAV/GPS WAAS

The GNS 430W and 530W represent upgraded versions of the GNS 430 and GNS 530 units described above. Physical appearance, control appearance, and operation are the same as the GNS 430 and GNS 530. Enhancements installed in the GNS 430W and GNS 530W units permit precision GPS navigation utilizing WAAS technology.

The GNS 430W series units are 6.25 inches wide 2.66 inches high. The display is a 128 by 240-pixel color LCD. The units include two removable data cards, one with Jeppesen database inserted in the left card slot and the second being a terrain database inserted in the right card slot.

The GNS 530W series units are 6.25 inches wide 4.60 inches high. The display is a 234 by 320-pixel color LCD. The units include two removable data cards, one with Jeppesen database inserted in the left card slot and the second being a terrain database inserted in the right card slot.

The GNS 430W and GNS 530W are WAAS GPS units that meet the requirements of Technical Standard Order (TSO) C146a and may be approved for IFR en-route, terminal, non-precision and precision approach operations when installed in reference to the OEM instructions as referenced in AML STC SA01933LA.

Both the GNS 430W and GNS 530W units include a VHF communications transceiver, VOR/Localizer and glideslope receiver. These are the same features and capabilities offered by the non-WAAS GNS 430 and GNS 530 versions.

The Garmin user guides and installation manuals for the GNS 430W COM/NAV/GPS GNS 530W COM/NAV/GPS receivers have additional information on the control functions and features. See Section 10-09 Troubleshooting Guide on page 19 of this chapter.

Section 10-04 Garmin SL30 COM/NAV Radio The SL30 COM/NAV transceiver provides radio communication between pilot and ground stations, and VOR/LOC/GS reception. Install the transceiver in either the COM1 or COM2 avionics panel position depending on the radio option package installed. Typical installations pair the SL30 as COM2 and a GNS series radio as COM1.

The description of the NAV subsystem is in Chapter 34.

The SL30 series radio is a slim line chassis design measuring 1.3 inches by 6.26 inches. The SL30 contains a 760-channel VHF communications transceiver with 200 channel VOR, Localizer, and Glide slope receivers. The Garmin user guide and installation manual for the SL30 COM/NAV receiver has additional information on the control functions and features.



Section 10-05 Garmin SL40 COM Radio The SL40 COM transceiver provides radio communication between pilot and ground stations. Installation can be in either the COM1 or COM2 stack position of the avionics panel depending on the radio option package installed. Typical installations pair a GNS series radio in the COM1 position with the SL40 radio in the COM2 position. The SL40 series radio is a slim line chassis design measuring 1.3 inches by 6.26 inches. The Garmin user guide and installation manual for the SL30 COM receiver has additional information on the control functions and features.

Section 10-06 Push-to-Talk Control of the Communications

Push-to-Talk control of the communication receivers is from a push-to-talk push button mounted to the yoke control. Because the button is part of the yoke control, procedures to remove and install the push-to-talk button are in Chapter 27 – Control Surfaces.

Section 10-07 Periodic Maintenance Periodic maintenance of this unit entails operational checks and inspections performed at intervals specified in the Liberty Maintenance Manual, Chapter 05 and in accordance with the operational check and inspection procedure in this section.

Section 10-08 VHF Transceiver Procedures This section contains the removal and installation procedures.

Only an appropriately equipped and certificated avionics maintenance facility can perform maintenance operations beyond simple removal or replacement of a communications transceiver.

Figure 23-6 SL30 Face Plate Key Slot

Figure 23-7 SL40 Face Plate Key Slot



TRANSCEIVER REMOVAL Perform the following procedure to remove the transceiver. Use this procedure for any of the radios installed in the avionics panel.

1. Check that both aircraft battery switch and avionics master switch are OFF.

2. Insert hex key (“3/32” Allen wrench”) into hole in faceplate of the radio and rotate counterclockwise until the retaining claw is released. (See illustration on previous page).

3. Slide the radio out of the mounting tray.

This completes the Transceiver Removal procedure.



TRANSCEIVER INSTALLATION Perform the following procedures to install the transceiver. Use this procedure for any of the radios installed in the avionics panel.


2. Check mating connectors on rear of radio and in mounting tray to check the integrity of all connections. Verify pins are straight and at the proper depth.

3. Verify that radio-retaining claw is in released position. If necessary, insert hex key into the hole in the radio faceplate and turn CCW.

4. Slide the radio into the mounting tray until connectors engage.

5. Insert hex key into the hole in the radio faceplate and turn counterclockwise until the radio firmly seats into the mounting tray.

6. Perform operation check of the COM/GPS system described in Transceiver Operation Check and Inspection on page 18 of this chapter.

This completes the Transceiver Installation procedure.



AVIONICS PANEL REMOVAL Perform the following procedure to remove the avionics panel from the airplane. Liberty Aerospace, Inc. recommends performing this procedure while sitting in the pilot’s seat. Have the block of soft foam cushioning for the avionics panel in your lap that it covers the yoke assembly.

This procedure describes the removal of all possible equipment available for the airplane. Some of the equipment and/or options called out in this procedure may not be in the airplane.

1. Remove instrument panel from airplane (see Chapter 31 – Indicators and Recording Systems).

2. Remove circuit breaker (CB) panel from airplane (see Chapter 24 – Electrical Power).

3. Remove the avionics radios from the avionics panel. To remove the radios, insert a hex key (“3/32” Allen wrench”) into the hole in faceplate of the radio and rotate counter-clockwise until the retaining claw is released. Slide the radio towards you and out of the radio tray.

Removal of the avionics radios reduces the weight of the avionics panel. This will make the panel easier to handle and less likely to damage the Instrument Panel Console assembly surfaces when removing the panel from the console.

4. Place the radio outside of the airplane.

5. Remove the eight screws holding in the avionics panel assy. Refer to for the location of the eight screws.

This completes the avionics panel removal procedure.



6. Disconnect the connectors P5354 and P5355 from the altitude encoder.

7. Disconnect the transponder antenna cable ATXP01 from the transponder tray.

8. Disconnect the marker beacon antenna cable AMB01B from the cable AMB01A.

9. Disconnect the RJ13 type (telephone jack) connector from the back of the Emergency Locator Transmitter, ELT, and remote unit.

10. Disconnect the COM-01 cable ACOM01A from the cable ACOM01B.

11. Disconnect the COM-02 cable ACOM02A from the cable ACOM02B.

12. Disconnect J41 from the connector P/J41on the bracket on the power distribution harness.

13. Disconnect J07 from the connector P/J07on the bracket on the power distribution harness.

14. Disconnect the NAV/LOC/GLS antenna cable, AVLOC01A from the antenna/signal splitter mounted on the side of the chassis of the avionics panel.

15. Remove the avionics panel and place face down in to a block of soft foam cushioning. Remove the avionics panel from the airplane, keeping the panel on its face into a block of soft foam cushioning.

This completes the avionics panel removal procedure.

Figure 23-8 Avionics Panel Showing the Location of the Screws



AVIONICS PANEL INSTALLATION Perform the following procedure to install the avionics panel.

1. Retrieve the avionics panel removed in step 5 in the procedure Avionics Panel on Page 15.

2. Connect J41 to P41 on the bracket on the right side of the power distribution harness.

3. Connect J07 to P07 on the bracket on the right side of the power distribution harness.

4. If the airplane has one or two Course Deviation Indicators, CDI, route their respective cable(s) from the avionics panel out the opening for the instrument panel.

5. Connect the COM-02 cable ACOM02A to the cable ACOM02B.

6. Connect the COM-01 cable ACOM01A to the cable ACOM01B.

7. Connect the RJ13 type (telephone jack) connector to the back of the Emergency Locator Transmitter remote unit.

8. Connect the marker beacon antenna cable AMB01B to the cable AMB01A.

9. Connect the transponder antenna cable ATXP01 to the transponder tray.

10. Connect the connectors P5354 and P5355 to the altitude encoder.

11. Connect the NAV/LOC/GLS antenna cable, AVLOC01A to the antenna/signal splitter mounted on the side of the chassis of the avionics panel.

12. Retrieve the avionics radios removed in step 4 in the procedure Avionics Panel on Page 15.

13. Check mating connectors on rear of radio and in the mounting tray to check the integrity of all connections. Check that pins are straight and at the proper depth.

14. Verify that radio-retaining claw is in released position. If necessary, insert hex key (“3/32” Allen wrench”) into the hole in the radio faceplate and turn counter-clockwise.

15. Slide the radio into the mounting tray until connectors engage.

16. Insert hex key (“3/32” Allen wrench”) into the hole in the radio faceplate and turn counter-clockwise until the radio is firmly seated in the mounting tray.

17. Install the circuit breaker panel in accordance with Chapter 24 –Electrical Power.

18. Install instrument panel in accordance with Chapter 31–Indicators and Recording Systems

This completes the avionics panel installation procedure.



TRANSCEIVER OPERATION CHECK AND INSPECTION Upon completing the installation of the transceiver, perform an operational check of the radio per the Garmin Ltd. OEM installation manual Post Installation Checkout procedure. Refer to Table 23-2 for applicable manual and section. In all cases, use the latest manual version.

MODEL DOCUMENT TITLE SECTION NOTES

SL40 560-0956-03 INSTALLATION MANUAL 2.0 Contact GARMIN Ltd. Dealer

SL30 560-0404-03 INSTALLATION MANUAL 2.0 Contact GARMIN Ltd. Dealer

GNS 430 190-00140-02 INSTALLATION MANUAL 5.0 Contact GARMIN Ltd. Dealer

GNS 430W 190-00356-02 INSTALLATION MANUAL 5.0 Contact GARMIN Ltd. Dealer

GNS 530 190-00181-02 INSTALLATION MANUAL 5.0 Contact GARMIN Ltd. Dealer

GNS 530W 190-00357-02 INSTALLATION MANUAL 5.0 Contact GARMIN Ltd. Dealer

This completes the Transceiver Operation Check and Inspection procedure.

Table 23-2 Table Showing the Documents Required to Perform the Operation Check and Inspection



Section 10-09 Troubleshooting Guide Table 23-3 gives a basic troubleshooting guide for the Garman radios.

Complaint Possible Cause Remedy Defective power supply wiring • Repair

Defective COM circuit breaker

• Replace in accordance with Liberty Maintenance Manual Chapter 24-Electrical Power

If other avionics are also without power: defective avionics master switch or relay

• Repair/replace

Unable to transmit or receive; communications transceiver display dark

Defective COM unit • Repair/replace Defective PTT switch on pilot side • Replace Unable to transmit from pilot

side

Defective wiring between pilot PTT switch and audio/intercom panel • Repair

Defective PTT switch on Copilot side • Replace Unable to transmit from copilot

side

Defective wiring between copilot PTT switch and audio/intercom panel

• Repair

Defective headset / microphone • Replace No modulation when transmitting from pilot side Defective wiring • Repair

Defective headset / Microphone • Replace No modulation when transmitting from copilot side Defective wiring • Repair

Antenna fault • Replace Microphone fault • Replace Weak transmission Defective COM unit • Repair/replace Antenna fault • Replace Headphone fault • Replace Defective COM unit • Replace

Weak reception

Audio panel fault • Repair/Replace

Section 10-10 COM/NAV/GPS Antenna This section details the information about the COM/NAV/GPS antennas installed on the airplane. Antenna installations are found on the top of the airplane aft of the doors. The forward antenna position is for COM/NAV/GPS 1 antenna, and the aft antenna position is for the COM/NAV/GPS 2 antenna.

Table 23-3 Troubleshooting Guide for the Garman Radios



The Liberty XL-2 uses one of two model COM/NAV/GPS antennas. The first is a model CI 2480-200 manufactured by Comant Industries. This model will support the GNS 430 and GNS 530 model NAV/COM/GPS (non-WAAS). This model antenna is designed for standard GPS radios. It is not able to support the higher precision requirements of GNS 430W and GNS 530W WAAS capable NAV/COM systems. GNS 430W and GNS 530W NAV/COM/GPS systems are supported by Comant Industries ComDat COM/NAV/GPS antenna model CI 2580-200 designed specifically to meet GPS WAAS Gamma 3 specifications. Both models of antenna are physically identical in appearance as show in Figure 23-9 but are not identical in performance.

Care must be taken during maintenance operations to verify the type of GPS navigation radio installed. WAAS and Non-WAAS GPS antenna models must match the radio they are connected to. Use of the incorrect antenna model will result in significant degradation of GPS navigation accuracy.

Some radio installation options on the XL-2 include the Garmin SL30 COM/NAV or SL40 COM radios. These units do not use the GPS portion of the antenna; therefore, they can connect to either model Comant COM/NAV/GPS antenna.

Prior to antenna removal and installation operations, verify avionics options and antennas installed. Connecting a non-WAAS radio to WAAS antenna or connecting a WAAS radio to a non-WAAS antenna will cause degraded GPS performance.

Section 10-11 Periodic Maintenance Periodic maintenance of this system entails inspections performed at intervals specified in the Liberty Maintenance Manual, Chapter 05 and in accordance with the inspection procedure in this section.

Figure 23-9 CI 2480-200 and CI 2580-200 Common Appearance



Section 10-12 COM/NAV/GPS Antenna Procedures For the two models of COM/NAV/GPS antennas that may be installed on the Liberty XL-2 inspection procedures are performed to determine if physical damage or deterioration has occurred that could degrade antenna performance. Antenna removal and replacement procedures are provided in the event replacement of damaged antenna is required.



MODEL CI 2480-200 ANTENNA REMOVAL Perform this procedure to remove the model CI 2480-200 Antenna. Refer to Figure 23-10 and Figure 23-11 during this procedure.

This section has removal and installation procedures for the COM/NAV/GPS antennas. Perform the following removal and installation procedures in the event there is an issue with the COM/NAV/GPS antenna. The procedure applies to both the forward and the aft antenna positions.

Failure to follow the correct removal and installation procedure will result in degraded antenna performance.

Before starting these procedures, the tail of the airplane requires support. Failure to support the airplane’s tail may cause damage to the airplane’s tail section while accessing any area aft of the passenger compartment.

GPS sections of the antennas are sensitive to Electrostatic Discharge (ESD). This procedure requires the use of ESD protection procedures to reduce the possibility of damage due to ESD.

Figure 23-10 CI 2480-200 COM/GPS Antenna Installation details



1. Position aircraft master switch to OFF.

2. Install a tail stand underneath the tail section of the airplane.

3. Connect an ESD wrist straps to a convenient chassis ground.

4. If removing the aft COM/NAV/GPS antenna, remove the cabin aft bulkhead access panel, by removing securing screw hardware, then go to step 6 of this procedure.

5. If working on the forward most COM/GPS antenna, remove the three screws securing the audio jack panel.

6. Disconnect COM antenna cable (ACOM01B or ACOM02B) from the COM connector.

7. Disconnect GPS antenna cable (AGPS01B or AGPS02B) from the GPS connector.

8. Remove four (4) antenna mounting screws and hardware.

Figure 23-11 View of the Underside of the Forward COM/NAV/GPS Antenna



Do not use any type of prying device to remove the antenna from the fuselage as this may cause damage to the fuselage.

9. Apply a gentle rocking motion and twisting motion to the antenna body to release bonding material and remove the antenna from the upper fuselage.

10. Install the ESD covers on to the connectors of the antenna.

This completes the Model CI 2480-200 Antenna Removal procedure



MODEL CI 2480-200 ANTENNA INSTALLATION Perform this procedure to install the model CI 2480-200 Antenna.


Failure to follow the correct removal and installation procedure will result in degraded antenna performance in the form of weak COM radio reception or transmission.





3. Mask-off an area of the fuselage that will be covered by the antenna.



4. Using fine (220-grit) sandpaper and/or a Scotch-Brite™ 7447 (maroon) hand pad, carefully clean residual sealant and debris within the rectangular area defined by the mounting holes. The goal here is to clean the carbon surface of debris without removing the carbon fibers.

5. Clean the surface with acetone and clean, lint free rags. Do not allow the acetone to air dry on the bonding surfaces. Dry the solvent using clean, lint free rags. Liberty Aerospace, Inc. recommends the use of two hands, one with a solvent dampened rag, and one following with a dry rag.

6. Continue wiping operation until the drying rag comes up clean.

7. Using de-natured alcohol, repeat the cleaning operations in steps 5 and 6.

8. Remove masking material.

9. Apply a bead of electrically conductive, MMS-040 Silver Coated Nickel Electrically Conductive RTV Silicone (Moreau Marketing & Sales, http:// http://www.rmoreau.com) along the inner edge of the gelcoat/carbon interface, taking care to stay a safe distance from the antenna cable hole. The goal here is to apply just enough RTV to get good contact between the antenna base and the carbon, but not so much that the RTV creeps out from under the antenna base when the antenna is installed. See Figure 23-13 for details of the location for the RTV sealant.

Do not allow the conductive RTV Silicone to come in contact with either the BNC or TNC RF connectors on the base of the antenna. The conductive RTV Silicone can short out the connector and can cause damage to the radio and/or the antenna.

Figure 23-12 Area of the Fuselage to Mask-Off to Protect the Fuselage



Silastic, RTV or Silicone-Based sealing/caulking compounds are not to be used around the base or over the screw fillets. The high dielectric content of these materials distort satellite reception at low angles of elevation.

10. Remove the protective ESD plugs.

11. Place the antenna through the fuselage.


13. If installing the aft COM/NAV/GPS antenna, remove the cabin aft bulkhead access panel, by removing securing screw hardware, then go to step 15 of this procedure.

14. If installing the forward COM/NAV/GPS antenna, remove the three screws securing the audio jack panel.

15. Mount the antenna using screws, washers, nuts. Gently tighten the mounting hardware so that uniform stress is placed on each side of the antenna. #10-32 screws DO NOT exceed 23 in-lbs of torque.

16. Connect the GPS coax antenna lead.

17. Connect the COM coax antenna lead

18. Check continuity between a mounting screw and the chassis for < 0.5 ohms resistance (0.003 ohms is ideal).

19. If working on the aft most COM/NAV/GPS antenna, install cabin aft bulkhead access panel then go to step 21 of this procedure.

20. If working on the forward most COM/NAV/GPS antenna, use the three screws to install the audio jack panel.


This completes the Model CI 2480-200 Antenna Installation procedure.

Figure 23-13 COM/GPS Antenna Conductive Sealant (bottom view)



MODEL CI 2580-200 ANTENNA REMOVAL Perform this procedure to remove the model CI 2580-200 Antenna. Refer to Figure 23-14 and Figure 23-15 during this procedure.





Figure 23-14 CI 2580-200 COM/GPS Antenna Installation details



Examine the screws used to mount the antenna to the fuselage. If the screws are the socket cap screw type, then replace the screws with #8-32 flat head screws.



3. .Connect an ESD wrist straps to a convenient chassis ground.

4. If working on the aft most COM/GPS antenna, remove the cabin aft bulkhead access panel, then go to step 6 of this procedure.

5. If working on the forward most COM/GPS antenna, remove the three screws securing the audio jack panel.

6. Disconnect COM antenna cable (ACOM01B or ACOM02B) from the COM connector.

7. Disconnect GPS antenna cable (AGPS01B or AGPS02B) from the GPS connector.

8. Remove four (4) antenna mounting screws and hardware.

Figure 23-15 View of the Underside of the COM/GPS Antenna



Do not use any type of prying device to remove the antenna from the fuselage as this may cause damage to the fuselage.

9. Apply a gentle rocking motion and twisting motion to the antenna body to release bonding material and remove the antenna from the fuselage.

10. Install the ESD covers on to the connectors of the antenna.

This completes the Model CI 2580-200 Antenna Removal procedure.



MODEL CI 2580-200 ANTENNA INSTALLATION Perform this procedure to install the model CI 2580-200 Antenna.




Before starting these procedures, the tail of the airplane requires support. Failure to support the airplane’s tail may cause damage to the airplane’s tail section while accessing any area aft of the passenger compartment



3. Mask-off an area of the fuselage that will be covered by the antenna.



4. Using fine (220-grit) sandpaper and/or a Scotch-Brite™ 7447 (maroon) hand pad, carefully clean residual sealant and debris within the rectangular area defined by the mounting holes. The goal here is to clean the carbon surface of debris without removing the carbon fibers.

5. Clean the surface with acetone and clean, lint free rags. Do not allow the acetone to air dry on the bonding surfaces. Dry the solvent using clean, lint free rags. Liberty Aerospace, Inc. recommends the use of two hands, one with a solvent dampened rag, and one following with a dry rag.

6. Continue wiping operation until the drying rag comes up clean.

7. Using de-natured alcohol, repeat the cleaning operations in steps 5 and 6.

8. Remove masking material.

9. Apply a bead of electrically conductive, MMS-040 Silver Coated Nickel Electrically Conductive RTV Silicone (Moreau Marketing & Sales, http:// http://www.rmoreau.com) along the inner edge of the gelcoat/carbon interface, taking care to stay a safe distance from the antenna cable hole. The goal here is to apply just enough RTV to get good contact between the antenna base and the carbon, but not so much that the RTV creeps out from under the antenna base when the antenna is installed. See Figure 23-13 for details of the location for the RTV sealant.

Do not allow the conductive RTV Silicone to come in contact with either the BNC or TNC RF connectors on the base of the antenna. The conductive RTV Silicone can short out the connector and can cause damage to the radio and/or the antenna.

Figure 23-16 Area of the Fuselage to Mask-Off to Protect the Fuselage



Silastic, RTV or Silicone-Based sealing/caulking compounds are not to be used around the base or over the screw fillets. The high dielectric content of these materials distort satellite reception at low angles of elevation

10. Remove the protective ESD plugs and place the antenna through the fuselage.


12. If installing the aft COM/NAV/GPS antenna, remove the cabin aft bulkhead access panel, by removing securing screw hardware, then go to step 14 of this procedure.

13. If installing the forward COM/NAV/GPS antenna, remove the three screws securing the audio jack panel.

14. Mount the antenna using screws, washers, nuts. Examine the screws used to mount the antenna to the fuselage. If the screws are the socket cap screw type, then replace the screws with #8-32 flat head screws. Gently tighten the mounting hardware so that uniform stress is placed on each side of the antenna. DO NOT exceed 23 in-lbs of torque.

15. Connect the GPS coax antenna lead.

16. Connect the COM coax antenna lead


18. If working on the aft most COM/GPS antenna, install cabin aft bulkhead access panel then go to step 20 of this procedure.

19. If working on the forward most COM/GPS antenna, use the three screws to install the audio jack panel.


This completes the Model CI 2580-200 Antenna Installation procedure.

Figure 23-17 COM/GPS Antenna Conductive Sealant



COM/NAV/GPS ANTENNA INSPECTION This procedure performs antenna inspections. Use this procedure in support of inspections identified in Liberty Maintenance Manual Chapter 05.

1. Position the aircraft on a level surface

2. Install a tail stand

The following steps require access to the aft fuselage section. Failure to install a tail stand prior to accessing this area could result in damage to the aircraft and possible injury.

3. Locate and remove the cabin aft access panel

4. Locate and remove the audio jack panel in the cabin ceiling

5. Inspect COM/NAV/GPS antenna 1, forward and 2 aft for the following:

• Loose or missing mounting hardware

• Corrosion of mounting hardware

• worn or loose connectors

• Damaged coaxial antenna cable

The following steps will inspect antenna exteriors for condition including presence of contamination around the antenna base. Antennas must not have any foreign material on the sides of the antenna base. GPS reception performance can be degraded by presence of foreign material. If material is found in this area remove it.

6. Inspect COM/NAV/GPS antenna 1, forward and 2, aft exterior installation for the following:

• Looseness

• Evidence if cracking

• Corrosion of mounting hardware

• Missing mounting hardware

• Inspect antenna and antenna base for presence of foreign material including dirt, oil, and wax and sealing material.



Contaminates Unacceptable Around Antenna Base

Unacceptable

Antenna Base Clearof Contaminates

Acceptable


Unacceptable


Acceptable


Unacceptable


Acceptable


8. Install audio jack panel in the cabin ceiling

9. Install cabin aft access panel

10. Remove tail stand

This completes the COM/NAV/GPS antenna inspection.

Figure 23-18 Antenna Contamination Inspection



Section 10-13 Troubleshooting Guide Complaint Possible Cause Remedy

In service wear • Replace Antenna cracked

Impact damage • Replace Physical antenna damage • Replace Coax cable connection fault • Repair

Poor antenna performance Excess bonding resistance • Remove, inspect and

reinstall antenna in accordance with Liberty Maintenance Manual Chapter 23

Loose antenna

Incorrect installation • Remove and reinstall in accordance with Liberty Maintenance Manual Chapter 23



Section 23-50 Audio Integration The XL2 airplane comes with an integrated audio selector panel/intercom system installed. The transmitter selector switch routes audio from the pilot and copilot microphones to the #1 or #2 communications transmitters. The receiver selector switches allow audio from the #1 or #2 communications receivers, the VHF navigation receiver(s), and the marker beacon receiver to be routed to the crew headsets.

The intercom system is of the voice actuated “hot mike,” type which means no additional action is required from the pilot or co-pilot for in-cockpit communications. Pressing the push-to-talk switches located on either control stick actuates the #1 or #2 communications transmitter as selected by the COM switch.

Headphones, including types with an integrated boom microphone, connect via standard headphone (1/4”) and aircraft microphone (3/16”) jacks. The location of these jacks is overhead between the pilot and co-pilot seats.

Section 50-01 GMA 340 AUDIO/ICS System The Liberty XL-2 is equipped with a Garmin model GMA 340 audio panel as standard equipment. This unit provides central audio management for all possible avionics options. LED illuminated push buttons allow audio selection for both NAV and COM audio. A large single button activation of the COM microphone and audio for up to three COM transceivers is provided. A fail-safe feature is incorporated that will connect the pilots headset directly to COM1 in the event power is interrupted or the unit is turned off. In the event of a power loss a fail-safe warning audio tone will be heard.

Figure 23-19 Audio Jack Panel



The audio panel includes a six position intercom system (ICS) with electronic cabin noise de-emphasis, two stereo music inputs and independent pilot and co-pilot volume controls. One stereo music input is available at the audio jack panel located in the cabin ceiling.

The XL-2 has audio panel installation is configured to make use of the pilot and co-pilot audio inputs only. Full intercom capability between these two stations is available.

Additional audio GMA340 audio panel control functions and feature may be found in the Garmin user guide and installation manual for this unit. See troubleshooting guide section below.

Section 50-02 Audio System Procedures This section has the procedures to remove and install the audio equipment.

Only an appropriately equipped and certificated avionics maintenance facility can perform maintenance operations beyond simple removal or installation of a communications transceiver.

Figure 23-20 GMA 340 Face Plate Key Slot



GMA 340 AUDIO PANEL REMOVAL This procedure performs audio pane until removal.


2. Insert hex key (“3/32” Allen wrench”) into the hole in the faceplate of the audio/intercom panel. Rotate counterclockwise until the retaining claw is released.

3. Slide the unit out of the mounting tray.

This completes the GMA 340 Audio Panel Removal procedure.



GMA 340 AUDIO PANEL INSTALLATION This procedure performs audio panel unit installation.

1. Check that both the aircraft battery switch and avionics master switch are OFF.

2. Check the mating connectors on the rear of the unit and in the mounting tray to check that no pins are bent or pushed back into the connector housing.

3. Verify that the retaining claw is in the released position. If necessary, insert a hex key into the hole in the faceplate and turn CCW.

4. Slide unit into the mounting tray until the connectors engage.

5. Insert a hex key into the hole in the faceplate and turn CW until the unit is firmly seated in the mounting tray.

6. Perform operation check of the audio system described in GMA340 Operation Check and Inspection on page 41 of this chapter.

This completes the GMA 340 Audio Panel Installation procedure.



GMA340 OPERATION CHECK AND INSPECTION Perform an operational check of the audio panel per the Garmin Ltd. OEM installation manual Post Installation Checkout procedure. Refer to Table 23-4 for applicable manual and section. Use the latest manual version.

Model Document Title Section Notes GMA 340 190-00149-01 Installation Manual 2.6 Contact Garmin Ltd. Dealer

This completes the GMA340 Operation Check and Inspection procedure.

Table 23-4 Manual to Use to Perform the Operation Check and Inspection



Section 50-03 Troubleshooting Guides Refer to Table 23-5 and Table 23-6 to resolve issues with the Garmin audio/intercom system. The manuals in Table 23-5 are reference to the latest versions of the Garmin Ltd. Manuals.

MODEL DOCUMENT TITLE NOTES GMA 340 190-00149-10 USER GUIDE Available at WWW.GARMIN.COM 190-00149-01 INSTALLATION MANUAL Contact Garmin Dealer

Complaint Possible Cause Remedy Defective power supply wiring • Repair Defective COM circuit breaker • Replace

If other avionics are also without power: defective avionics master switch or relay

• Replace Unable to transmit or receive; communications transceiver display dark

Defective radio unit • Repair/replace Defective PTT switch on pilot side • Replace

Unable to transmit from pilot side Defective wiring between pilot PTT

switch and audio/intercom panel • Repair

Defective PTT switch on copilot side • Replace Unable to transmit from copilot side

Defective wiring between copilot PTT switch and audio/intercom panel

• Repair

Defective headset or microphone. • Replace No modulation when transmitting from pilot side Defective wiring • Repair

Defective headset or microphone. • Replace No modulation when transmitting from copilot side Defective wiring • Repair

Defective COM radio • Repair/Replace Headset microphone fault • Replace

Transmission reported weak by other stations, receive mode OK

Audio jack fault • Repair/replace Defective COM radio • Repair/replace Headphone fault • Replace

Receive mode weak / noisy

Audio jack fault • Repair/replace Defective COM antenna, coaxial cable, or connectors

• Repair/replace

Headset fault • Replace

Transmit and receive both weak or noisy

Audio panel fault • Repair/replace Intercom system inoperative, transmit mode functional

Defective audio/ICS panel • Repair/replace

Table 23-5 Garmin Troubleshooting Guide Reference

Table 23-6 Troubleshooting Guide for the XL2 Airplane COM/GPS Systems