-
190-00993-04 November 2009 Rev. 2
GTS 8XX
AML STC Installation Manual
Part 2
Mechanical Installation
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GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page A
Rev. 2 190-00993-04
© 2009
Garmin Ltd. or its subsidiaries All Rights Reserved
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RECORD OF REVISIONS
Revision Revision Date Description
1 11/5/09 Initial Release
2 11/30/09 Updated to clarify installation requirements and incorporate feedback from Garmin Engineering.
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Page B GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
190-00993-04 Rev. 2
Revision Page
Number(s) Section Number
Description of Change
2-2 2.1.1 Added Epoxy primer specification.
2-3 2.1.1 Added requirement regarding installing GTS in composite areas.
2-5 2.2 Updated Figure 2-4 and Figure 2-5.
2-6 2.2 Added Epoxy primer specification.
2-7 2.3 Added reference to Appendix A of GTS-IM1.
A-1, A-2 A.1 Revised static test loads.
A-2 A.2 Clarified load application procedure.
B-2 Appendix B Updated Figure B-2.
C-1 Appendix C Updated Figure C-1.
C-4 Appendix C Updated Figure C-4.
C-5 Appendix C Updated Figure C-5.
C-6 Appendix C Updated Figure C-6.
C-7 Appendix C Removed Figure C-7.
D-4 Appendix D Updated Figure D-4.
D-5 Appendix D Updated Figure D-5.
E-1 Appendix E Updated Figure E-1.
E-2 Appendix E Updated Figure E-2.
E-4 Appendix E Updated Figure E-4.
F-1 Appendix F Updated Figure F-1.
F-3 Appendix F Updated Figure F-3.
F-4 Appendix F Updated Figure F-4.
F-6 Appendix F Updated Figure F-6.
F-7 Appendix F Updated Figure F-7.
F-8 Appendix F Updated Figure F-8.
2
F-10 Appendix F Updated Figure F-10.
DOCUMENT PAGINATION
Section Pagination
Table of Contents i - ii
Section 1 1-1 through 1-2
Section 2 2-1 through 2-8
Appendix A A-1 through A-2
Appendix B B-1 through B-2
Appendix C C-1 through C-8
Appendix D D-1 through D-6
Appendix E E-1 through E-4
Appendix F F-1 through F-12
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GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page i
Rev. 2 190-00993-04
TABLE OF CONTENTS
SECTION PAGE
1 INTRODUCTION...............................................................................................................................1-1
1.1 Installation Manual Format ............................................................................................................1-1
2 INSTALLATION PROCEDURE......................................................................................................2-1
2.1 GTS 8XX Location and Mounting .................................................................................................2-1
2.1.1 Requirements for all GTS 8XX Installations .......................................................................2-2
2.1.2 Mounting Bracket—Attachment to Stringers or Longerons ................................................2-3
2.1.3 GTS 8XX Mechanical Installation Procedure......................................................................2-4
2.2 GPA 65 Location and Mounting ....................................................................................................2-5
2.2.1 GPA 65 Mechanical Installation Procedure .........................................................................2-6
2.3 Antenna Location and Mounting....................................................................................................2-7
2.4 Weight and Balance........................................................................................................................2-8
APPENDIX A CONSTRUCTION AND VALIDATION OF STRUCTURES ...............................A-1
A.1 Static Test Loading........................................................................................................................A-1
A.2 Determine Static Load Capability .................................................................................................A-2
APPENDIX B GENERAL INSTALLATION DETAILS................................................................. B-1
APPENDIX C GTS 8XX HORIZONTAL MOUNT DETAILS.......................................................C-1
APPENDIX D GTS 8XX VERTICAL MOUNT DETAILS .............................................................D-1
APPENDIX E GPA 65 INSTALLATION DETAILS ....................................................................... E-1
APPENDIX F GA 58 ANTENNA INSTALLATION DETAILS ..................................................... F-1
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LIST OF FIGURES
Figure 1-1. Installation Manual Documentation Format............................................................................1-1
Figure 2-1. GTS 8XX Horizontal Mount on a Horizontal Surface............................................................2-1
Figure 2-2. GTS 8XX Horizontal Mount on a Vertical Surface ................................................................2-1
Figure 2-3. GTS 8XX Vertical Mount on a Horizontal Surface ................................................................2-2 Figure 2-4. GPA 65 Mounting to a Vertical Surface .................................................................................2-5
Figure 2-5. GPA 65 Mounting to a Horizontal Surface .............................................................................2-5
Figure A-1. Upward Static Load Test .......................................................................................................A-3 Figure A-2. Forward Static Load Test ......................................................................................................A-3
Figure B-1. GTS 8XX Mounting Hole Pattern – Vertical and Horizontal Mount.................................... B-1
Figure B-2. General Bracket Design for GTS 8XX.................................................................................. B-2
Figure C-1. GTS 8XX in Horizontal Mount – Center of Gravity............................................................. C-1
Figure C-2. GTS 8XX Horizontal Mount Outline .................................................................................... C-2
Figure C-3. GTS 8XX Horizontal Mount – Attached to Stringers ........................................................... C-3
Figure C-4. GTS 8XX Horizontal Mount – Stringer Installation ............................................................. C-4
Figure C-5. GTS 8XX Horizontal Mount – Floor Panel Installation........................................................ C-5
Figure C-6. GTS 8XX Horizontal Mount – Fabricated Installation Bracket ............................................ C-6
Figure D-1. GTS 8XX Vertical Mount – Center of Gravity .....................................................................D-1
Figure D-2. GTS 8XX Vertical Mount Installation Drawing ...................................................................D-2
Figure D-3. GTS 8XX Vertical Mount Example ......................................................................................D-3
Figure D-4. GTS 8XX Vertical Mount – Fabricated Installation Bracket ................................................D-4
Figure D-5. GTS 8XX Vertical Mount – Attached to Existing Structure.................................................D-5
Figure E-1. GPA 65 PA LNA Outline Drawing ....................................................................................... E-1
Figure E-2. GPA 65 – Attached to Installation Bracket............................................................................ E-2
Figure E-3. GPA 65 Mount Example........................................................................................................ E-3 Figure E-4. GPA 65 Example Details ....................................................................................................... E-4
Figure F-1. GA 58 Antenna Outline ......................................................................................................... F-1
Figure F-2. GA 58 Doubler Example........................................................................................................ F-2
Figure F-3. Antenna Doubler with Joggles Installed on Skin/Fuselage Structure .................................... F-3
Figure F-4. Isometric View of Joggled Antenna Doubler Assembly........................................................ F-4
Figure F-5. View of GA 58 Joggled Antenna Doubler from Inside of Fuselage...................................... F-5
Figure F-6. GA 58 Installation Between Stringers.................................................................................... F-6
Figure F-7. GA 58 Antenna Flanged Doubler Design Detail ................................................................... F-7 Figure F-8. Flanged Doubler Assembly with Nutplates ........................................................................... F-8
Figure F-9. GA 58 Antenna Flanged Doubler Design Detail ................................................................... F-9
Figure F-10. GA 58 Antenna Installation on Flanged Doubler .............................................................. F-10
Figure F-11. View of GA 58 Antenna Installation ................................................................................. F-11
LIST OF TABLES
Table 2-1. Weight of GTS 8XX and Equipment........................................................................................2-8
Table 2-2. Sample Weight and Balance Calculation .................................................................................2-8
Table A-1. Static Test Loads for Vertical Mounting Rack .......................................................................A-1 Table A-2. Static Test Loads for Horizontal Mounting Rack...................................................................A-1
Table A-3. Static Loads for GPA 65.........................................................................................................A-2
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GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page 1-1
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1 Introduction
This manual covers instructions on the mechanical installation of the GTS 8XX traffic device. This
manual also includes requirements for selection of proper locations in the aircraft, as well as requirements
for supporting structure.
1.1 Installation Manual Format
This installation manual is only a part of the full documentation required for installation of the GTS 8XX.
The installation is broken into four separate parts with a separate manual for each part of the installation.
This manual provides instructions pertaining to the mechanical installation. For other aspects of the installation, see the pertinent installation manual. Be sure to read each of the separate manuals before
beginning the installation. Installation Manual part numbers are contained in Figure 1-1.
Figure 1-1. Installation Manual Documentation Format
Part 1: Overview and Limitations describes the pre-installation information necessary to plan for installing the GTS 8XX system into an aircraft. For brevity, will be referred to as GTS-IM1.
Part 2: Mechanical Installation describes location considerations and instructions pertaining to the
mechanical installation of the GTS 8XX and related hardware. Referred to as GTS-IM2.
Part 3: Electrical Installation describes cabling and wiring requirements, electrical harness build-up and
installation, as well as electrical interconnect information. Referred to as GTS-IM3.
Part 4: Configuration and Checkout describes software loading and configuration and system checks required prior to operation of the GTS 8XX. Referred to as GTS-IM4.
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2 Installation Procedure
2.1 GTS 8XX Location and Mounting
Refer to GTS-IM1 for information on selecting a proper mounting location for the GTS 8XX. The
GTS 8XX should be mounted to a surface known to have sufficient structural integrity to withstand
additional inertial forces imposed by a 10.5 pound unit (weight of the GTS 8XX and a vertical mounting rack), or an 11.3 pound unit (GTS 8XX and a horizontal mounting rack). If it is necessary to build a shelf
or bracket to mount the GTS 8XX or if it is not certain that the chosen location is of sufficient structural
integrity, refer to Appendix A for validation of rack mounting structures and determining static load capability.
If a horizontal mounting rack is chosen for the installation, the GTS 8XX can be mounted to a vertical or
horizontal surface. It can be mounted to the top of pre-existing or fabricated structure or to the bottom (such that it hangs) of pre-existing or fabricated structure. See Figure 2-1 and Figure 2-2.
UP
SIDEFWD
UP
SIDEFWD
GTS 8XX UNIT CAN BE MOUNTED IN A
HORIZONTAL RACK WITH CONNECTOR
FACING EITHER SIDE ON A HORIZONTAL
SURFACE.
GTS 8XX UNIT CAN BE MOUNTED IN A
HORIZONTAL RACK WITH CONNECTOR
FACING FORE OR AFT ON A HORIZONTAL
SURFACE
Figure 2-1. GTS 8XX Horizontal Mount on a Horizontal Surface
UP
SIDEFWD
UP
SIDEFWDGTS 8XX UNIT CAN BE MOUNTED IN A
HORIZONTAL RACK WITH CONNECTOR
FACING FORE OR AFT ON A VERTICAL
SURFACE
GTS 8XX UNIT CAN BE MOUNTED IN A
HORIZONTAL RACK WITH CONNECTOR
FACING UP OR DOWN ON A VERTICAL
SURFACE
Figure 2-2. GTS 8XX Horizontal Mount on a Vertical Surface
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If a vertical mounting rack is chosen for the installation, the GTS 8XX can only be mounted to a
horizontal surface. Do not mount the GTS 8XX with vertical mounting rack to a vertical surface. See Figure 2-3.
UP
SIDEFWD
GTS 8XX UNIT CAN BE MOUNTED IN A
VERTICAL RACK WITH CONNECTOR
FACING FORE OR AFT ON A HORIZONTAL
SURFACE.
UP
SIDEFWD
GTS 8XX UNIT CAN BE MOUNTED IN A
VERTICAL RACK WITH CONNECTOR
FACING TO EITHER SIDE ON A
HORIZONTAL SURFACE
Figure 2-3. GTS 8XX Vertical Mount on a Horizontal Surface
2.1.1 Requirements for all GTS 8XX Installations
In order to satisfy the structural requirements for the operation of the GTS 8XX the following conditions
must be met:
1. If support racks, brackets or shelves need to be fabricated, they should be fabricated and attached
to the aircraft metallic structure in accordance with the methods outlined in AC43.13-2B Chapter
2, AC43.13-1B Chapter 4, and the following requirements:
a. Material shall be 2024-T3 sheet aluminum (bare or Clad)
b. Material shall have corrosion protection. Apply zinc chromate primer that meets FED
STD TT-P-1757, or epoxy primer that meets MIL-P-23377, or other corrosion protection methods listed in the aircraft’s maintenance manual.
c. Material shall be a minimum of 0.063” thick
d. Use sheet metal techniques (bend radius, fillets, etc) appropriate to the material thickness and type.
If existing structure allows spans of greater than 12” in any direction, stiffeners may be required
to provide adequate support. Flanges on a fabricated bracket may be required to help stiffen the bracket. Refer to Appendix B for additional details.
2. If existing structure is to be used for mounting the GTS 8XX, it must meet the following requirements:
a. Sheet aluminum structure must be a minimum of 0.063” thick
b. Existing Aluminum honeycomb avionics shelf material may be used. The side of the panel that mounts the GPA must be electrically bonded via fasteners or bond straps (min
width of 3/8inches and no longer than 4 inches) to metallic structure of the aircraft. Refer
to GTS-IM3 section 2 for additional details.
c. If existing structure allows spans greater than 12” in any direction, stiffeners may be
required to provide adequate support
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3. Any supporting structure must be rigidly attached to the aircraft primary structure through
structural members capable of supporting substantial loads such as braces, stringers, flanges, longerons, etc. Refer to Appendix A for more information on determining the strength of a
structural member. Avoid areas that are prone to vibration (e.g., areas close to engine mounts and
landing gear).
4. If a new mounting platform is fabricated for the GTS 8XX, the plate shall not span greater than
12” in width or length without direct attachment to primary structure. If mounting platform does
span greater than 12”, add necessary stringers, doublers, bulkhead flange reinforcements, etc., to provide adequate support.
5. Maintain a minimum of 3” between the edge of the mounting rack nearest the connector and any nearby objects to ensure clearance for the connectors, wire harness and antenna cables.
6. Final installation must be resistant to visual deflection during the validation of structures test in
Appendix A.
7. The GTS 8XX must be electrically bonded to the aircraft metallic structure. Brackets that the
GTS 8XX is mounted to shall be electrically bonded to structure. No special surface preparation
is required if the bracket is installed to metallic structure with four or more rivets. When nutplates are used to attach brackets to structure the nutplates are inherently bonded via the rivets that
attach them. Electrical bond preparation may be required under the head of the fastener that
screws into the nutplate. Refer to GTS-IM3 section 2 for additional details.
8. The GTS 8XX and its wiring may not be installed in the area fully enclosed by exterior skins
constructed of composite laminate.
2.1.2 Mounting Bracket—Attachment to Stringers or Longerons
Refer to Appendix C for the following section. The following items should be considered when creating a mounting bracket to span between stringers or longerons:
• Mounting bracket requirements should follow conditions noted in section 2.1.1, unless otherwise
indicated.
• Distance between stringers or longerons should be less than 16.0 inches. For a distance between
12.0 and 16.0 inches, use a stiffener down the centerline of the mounting hole pattern. At a
minimum, the stiffener should be made of 0.75 x 0.50 x 0.063” angle, with the 0.75” leg used for
attachment to the mounting bracket, and should run the length of the bracket. Nutplates for the GTS 8XX Mounting Plate may be attached directly to the stiffener. Use MS20426AD3 or
MS20426AD4 rivets to secure the stiffener to the mounting bracket. The vertical leg of the
stiffener must be at least 0.25” from the skin of the aircraft.
• Ensure at least 3 inches beyond the connector end of the GTS 8XX remains clear for connector
and wire harness.
• Fabricate a U-shaped mounting bracket keeping edge flanges as short as possible. The flange
should be no more than 0.5 inches higher than the stringers. See figure C-3.
• Minimal access to underside of bracket requires use of blind fasteners for the bracket to structure
and for the GTS 8XX to the bracket. Structural fasteners such as NAS9301B (Cherry Max
CR3213) rivets should be used. Do not use non-structural blind rivets.
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2.1.3 GTS 8XX Mechanical Installation Procedure
Follow these steps to properly install the GTS 8XX:
1. Position the GTS 8XX mounting rack to the mounting panel and transfer the hole-pattern to the mounting plate, 4 places in the vertical orientation; 6 places in the horizontal orientation.
Refer to Figure B-1 for the correct mounting hole pattern.
2. Remove the GTS 8XX, drill the marked hole-pattern (0.166 inch diameter holes preferred) and rivet nutplates (MS21047 or noted equivalent) with rivets (countersunk rivets). Acceptable
hardware is identified in Appendix C and Appendix D. Ensure that installed rivets are flush
with the installation panel. Remove any burrs or excess rivet heads. Perform a structural validation per Appendix A.
3. Install the GTS 8XX to the mounting plate using MS35206, AN525, or NAS602 # 8-32 screws (4 required for vertical orientation; 6 required for horizontal orientation). The recommended
torque is 12-15 inch lbs.
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2.2 GPA 65 Location and Mounting
Determine a suitable location for the GPA 65 unit. Refer to GTS-IM1 section 2 for information on
determining a suitable mounting location. The GPA 65 can be mounted on either a vertical or horizontal surface. See Figure 2-4 and Figure 2-5.
UP
SIDEFWD
UP
SIDEFWD
GPA 65 CAN BE MOUNTED WITH
CONNECTOR FACING FORE OR AFT ON A
VERTICAL SURFACE
GPA 65 CAN BE MOUNTED
WITH CONNECTOR FACING
UP OR DOWN ON A
VERTICAL SURFACE
Figure 2-4. GPA 65 Mounting to a Vertical Surface
UP
AFTSIDE
UP
AFTSIDE
GPA 65 CAN BE MOUNTED
WITH CONNECTOR FACING
TO ONE SIDE ON A
HORIZONTAL SURFACE
GPA 65 CAN BE MOUNTED
WITH CONNECTOR FACING
FORE OR AFT ON A
HORIZONTAL SURFACE
Figure 2-5. GPA 65 Mounting to a Horizontal Surface
The GPA 65 must be mounted to a metallic surface known to have sufficient structural integrity to withstand additional inertial forces imposed by a 1.9 pound unit (weight of the GPA 65). If it is necessary
to build a shelf or bracket to mount the GPA 65 or if it is not certain that the chosen location is of
sufficient structural integrity, refer to Appendix A.
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In order to satisfy the structural requirements for the operation of the GPA 65 the following conditions
must be met:
1. If support racks, brackets or shelves need to be fabricated, they should be fabricated and attached
to the aircraft structure in accordance with the methods outlined in AC43.13-2B Chapter 2,
AC43.13-1B Chapter 4, and the following requirements:
a. Material shall be 2024-T3 sheet aluminum (bare or Clad)
b. Material shall have corrosion protection. Apply zinc chromate primer that meets FED
STD TT-P-1757, or epoxy primer that meets MIL-P-23377, or other corrosion protection methods listed in the aircraft’s maintenance manual.
c. Material shall be a minimum of 0.040” thick
d. Use sheet metal techniques (bend radius, fillets, etc) appropriate to the material thickness
and type.
2. If existing structure is to be used it must meet the following requirements:
a. Sheet aluminum structure must be a minimum of 0.040” thick.
b. Structural Aluminum honeycomb avionics shelf material may be used.
3. Any supporting structure must be rigidly attached to the aircraft primary structure through structural members capable of supporting substantial loads such as braces, stringers, flanges,
longerons, etc. Refer to Appendix A for more information on determining the strength of a
structural member. The side of the panel that mounts the GPA must be electrically bonded via fasteners or bond straps (min width of 3/8inches and no longer than 4 inches) to metallic structure
of the aircraft. Refer to GTS-IM3 section 2 for additional details.
4. Mounting platform shall not span greater than 16” in width or length without direct attachment to primary structure. If mounting platform does span greater than 16”, add necessary stringers,
doublers, bulkhead flange reinforcements, etc., to provide adequate support.
5. Maintain a minimum of 3” between the each end of the GPA 65 and any object to ensure clearance for the connectors, wire harness and antenna cables.
6. The GPA 65 must be electrically bonded to the aircraft metallic structure. Brackets that the GTS
8XX is mounted to must be electrically bonded to structure. No special surface preparation is required if the bracket is installed to metallic structure with four or more rivets. When nutplates
are used to attach brackets to structure the nutplates are inherently bond via the rivets that attach them. Electrical bond preparation may be required under the head of the fastener that screws into
the nutplate. Refer to GTS-IM3 section 2 for additional details.
2.2.1 GPA 65 Mechanical Installation Procedure
Follow these steps to properly install the GPA 65 on the mounting plate:
a. Position the GPA 65 to the mounting panel and transfer the hole-pattern to the mounting
plate from the flanges. See Appendix E for installation drawings.
b. Remove the GPA 65, drill the marked hole-pattern (0.166 inch diameter holes) and rivet nut plates (MS21047 or noted equivalent) with rivets (countersunk rivets). Acceptable
hardware is identified in Figure E-2. Ensure that installed rivets are flush with the
installation panel. Remove any burrs or excess rivet heads. Perform a structural validation per Appendix A.
c. Install GPA 65 to the mounting plate using MS35206, AN525, or NAS602 # 8-32 screws
(4 required). The recommended torque is 12-15 inch lbs.
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2.3 Antenna Location and Mounting
Determine a suitable location for the antenna(s). Refer to GTS-IM1 for placement information, including
lightning zoning information covered in GTS-IM1 Appendix A.
Refer to the GA 58 installation drawings shown in Appendix F.
CAUTION
Do not use construction grade RTV sealant or sealants containing acetic acid. These
sealants may damage the electrical connections to the antenna. Use of these types of
sealants may void the antenna warranty.
1. Refer to the GA 58 installation drawings shown in Appendix F for the mounting cutout.
2. For metal skin aircraft, do not remove paint on outer skin of aircraft under the footprint of the
antenna baseplate unless necessary to meet bonding requirements. The painted surface prevents
corrosion and should be left intact if possible. If paint needs to be removed for bonding, be
careful to avoid excessive chipping or cracking beyond the antenna baseplate, which could
become a source for corrosion. Refer to GTS-IM3 section 2.4.1 for bonding requirements.
3. Install a doubler plate to reinforce the aircraft skin . The metal doubler plate must be mounted
such that it is electrically bonded to the structure. The doubler plate provides the electrical bond
necessary for the antenna. See Appendix F for structural details.
4. Place the supplied O-ring, 251-00011-00, in the groove on the bottom surface of the antenna.
5. Mount the antenna to the airframe with the four supplied #8-32 stainless steel screws, 211-60209-
16. Washers and locking nuts or nut plates (not provided, may be part of doubler plate) are required to secure the antenna. Apply torque evenly across all mounting screws. The
recommended torque is 12-15 inch lbs. Note that longer screws may be necessary, depending on
specific aircraft installation details. Ensure a minimum of 2 threads extend beyond the nut (or
nutplate). If necessary, replace the screws with length-appropriate stainless steel or cad-plated
steel hardware.
6. Ensure that the antenna base and aircraft skin are in continuous contact.
7. Verify the electrical bond of the antenna. See GTS-IM3 section 2.4.1 for bonding requirements.
8. Fillet seal the antenna and gasket to the fuselage using a good quality electrical grade sealant,
such as Dow 738 (MIL-A-46146) or equivalent. Run a bead of the sealant along the edge of the
antenna where it meets the exterior aircraft skin. Use caution to ensure that the antenna connector
is not contaminated with sealant. Seal the mounting screws with sealant.
9. Connect the four antenna cables ensuring each cable is connected to the correct antenna
connector. Each antenna connector and cable has a matching color band.
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2.4 Weight and Balance
Weight and balance computation is required after the installation of the GTS 8XX. Follow the guidelines
as established in AC 43.13-1B, Chapter 10, Section 2. Make appropriate entries in the equipment list indicating items added, removed or relocated along with the date accomplished. Include your name and
certificate number in the aircraft records.
Table 2-1 identifies the weight of the new GTS 8XX equipment. Refer to the appropriate Appendix for
equipment center of gravity (CG) dimensions. For example weight and balance data, see Table 2-2.
Table 2-1. Weight of GTS 8XX and Equipment
Item Weight Dimensions and CG
GTS 8XX 8.9 lbs (4.04 kg) See Appendix D
GTS 8XX, vertical mounting rack 10.7 lbs (4.85 kg) See Appendix D
GTS 8XX, horizontal mounting rack 11.5 lbs (5.22 kg) See Appendix C
GPA 65 1.9 lbs (0.86 kg) See Appendix E
GA 58 antenna 0.82 lbs (0.372 kg) See Appendix F
Table 2-2. Sample Weight and Balance Calculation
Previous Aircraft Weight and Balance Useful Load Empty Weight C.G. Moment
Calculated 03/10/09 1093.3 2306.70 138.83 320239
Description of items removed from aircraft Weight Arm Moment
Total removed 0 0
Description of items added to aircraft Weight Arm Moment
GTS 850 and horizontal mounting rack 11.5 159.10 1829.65
GA 58 antenna with screws 0.82 120.00 98.4
GPA 65 PA/LNA 1.9 119.30 226.67
Total added 14.22 2154.72
Change +14.22 2154.72
New Aircraft Weight and Balance Useful Load Weight C.G. Moment
11/16/2009 1079.08 2320.92 138.90 322394
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Appendix A Construction and Validation of Structures
A.1 Static Test Loading
This appendix includes information necessary for testing load-carrying capabilities of equipment
mounting structures, such as shelves, mounting plates and mounting brackets, used to mount the
GTS 8XX remote mounting tray and GPA 65.
Baggage compartments and cabins or cockpit floors are good mounting platforms provided the floor
attachments meet the strength requirements. If support racks, brackets or shelves need to be fabricated,
they should be fabricated and attached to the aircraft structure in accordance with the methods outlined in AC 43.13-2B Chapter 2. After the structure is installed, it should be tested as outlined in AC 43.13-2B
Chapter 1 to verify that it is capable of supporting the required loads.
The GTS 8XX/GPA 65 installation must be capable of withstanding the Ultimate Load Factors listed in the applicable table below for at least 3 seconds in each direction specified without damage or permanent
deformation. Note that these required loads differ somewhat from those normally required for equipment installations.
The combined weight of the GTS 8XX, connector and vertical mounting rack is 10.7 lbs. The static loads
which must be applied (Load Factor x 10.7 lbs.) will be the following:
Table A-1. Static Test Loads for Vertical Mounting Rack
Direction of Force Load Factor Static Test Load
(Load Factor x (GTS 8XX + Vertical Mounting Rack Weight))
Downward 9.0 g (9.0 x 10.7) = 96.30 lbs
Upward 4.5 g (4.5 x 10.7) = 48.15 lbs
Sideward 4.5 g (4.5 x 10.7) = 48.15 lbs
9.0 g (Note 1) (9.0 x 10.7) = 96.30 lbs Forward
18.0 g (Note 2) (18.0 x 10.7) = 192.60 lbs
Notes:
1. Applicable when GTS 8XX unit is mounted outside the cabin 2. Applicable when GTS 8XX unit is mounted within the cabin.
The combined weight of the GTS 8XX, connector and horizontal mounting rack is 11.5 lbs. The static
loads which must be applied (Load Factor x 11.5 lbs.) will be the following:
Table A-2. Static Test Loads for Horizontal Mounting Rack
Direction of Force Load Factor Static Test Load
(Load Factor x (GTS 8XX + Horizontal Mounting Rack Weight))
Downward 9.0 g (9.0 x 11.5) = 103.5 lbs
Upward 4.5 g (4.5 x 11.5) = 51.75 lbs
Sideward 4.5 g (4.5 x 11.5) = 51.75 lbs
9.0 g (Note 1) (9.0 x 11.5) = 103.5 lbs Forward
18.0 g (Note 2) (18.0 x 11.5) = 207.00 lbs
Notes:
1. Applicable when GTS 8XX unit is mounted outside the cabin 2 Applicable when GTS 8XX unit is mounted within the cabin
-
Page A-2 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
The combined weight of the GPA 65, connector and vertical mounting rack is 1.9 lbs. The static loads
which must be applied (Load Factor x 1.9 lbs.) will be the following:
Table A-3. Static Loads for GPA 65
Direction of Force Load Factor Static Test Load
(Load Factor x (GPA 65 Weight))
Downward 9.0 g (9.0 x 1.9) = 17.1 lbs
Upward 4.5 g (4.5 x 1.9) = 8.55 lbs
Sideward 4.5 g (4.5 x 1.9) = 8.55 lbs
9.0 g (Note 1) (9.0 x 1.9) = 17.1 lbs Forward
18.0 g (Note 2) (18.0 x 1.9) = 34.2 lbs
Notes:
1. Applicable when GPA 65 unit is mounted outside the cabin 2. Applicable when GPA 65 unit is mounted within the cabin
A.2 Determine Static Load Capability
A recommended method of determining the static load capability is as follows:
1. Mark and drill the holes where the GTS 8XX equipment rack or GPA 65 will be mounted, whichever is applicable to the installation.
2. Install four (six for the horizontal rack) 8-32 machine screws (MS35206, AN525, NAS602, or equivalent) in the holes which will be used to mount the GTS 8XX equipment rack or GPA 65
using washers, nuts and nutplates to mount the equipment rack to the mounting surface. Note
that some means of locking fastener must be used, e.g. either lock nuts or steel nuts with lock washers.
3. For testing downward loading, place shot bags or other suitable weights totaling the required
downward load specified in Table A-1 or Table A-2 for the GTS 8XX or Table A-3 for the GPA 65. Place the load within the footprint outlined by the screw holes or use a calibrated force gauge
at the location of the center of gravity where the unit is mounted. Note that if the GPA 65 is
mounted on the fuselage ceiling, shot bags can be hung from the mounting location.
4. Verify there is no damage or permanent deformation of the structure after 3 seconds.
5. Fasten a 36 inch loop of suitable material such as fishing line, braided wire, or other similar
material having a breaking strength of at least 250 lbs diagonally between two of the screws. Then fasten another loop diagonally between the other two screws, adjusting the length of the
loop so it exactly matches the first.
6. Hook a calibrated force gauge through both loops and apply a sustained pull for at least 3 seconds in each of the other three directions (upward, sideward and forward) at the calculated forces in the
tables above. Refer to Figure A-1 and Figure A-2.
7. Examine the support structure carefully. If there has been damage or permanent deformation, the structure is not suitable and must be replaced with one that is strong enough to withstand the test
loads. Examine all aircraft stringers, bulkheads and skin surfaces, which may have direct or indirect contact with the fabricated shelf. If it is determined that no damage or permanent
deformation has occurred, the structure is of sufficient strength and the GTS 8XX equipment rack
or GPA 65 may be permanently mounted to it.
-
GTS 8XX AML STC Installation Manual Page A-3
190-00993-04 Rev. 2
Figure A-1. Upward Static Load Test
Figure A-2. Forward Static Load Test
-
Page A-4 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
This page intentionally left blank
-
GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page B-1
Rev. 2 190-00993-04
Appendix B General Installation Details
2.00
8.10
2.752.75
8.10 12.80
2.40
0.46
6.42
Ø0.1740.164
, 6XØ0.1740.164
, 4X
2.40
1.99
2.81
0.40
CONNECTOR AREACONNECTOR AREA
1.99
12.80
Figure B-1. GTS 8XX Mounting Hole Pattern – Vertical and Horizontal Mount
-
Page B-2 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
8 - 12"
12-16"
UP TO 8",
NO EXTRA FLANGES
8" UP TO 12",
FORWARD AND AFT
FLANGES
12" UP TO 16"
FORWARD AND AFT
FLANGES AND
STIFFENER (LONGEST
BRACKET DIMENSION)
0.25" MIN.
DEFLECTION GAP
MAX. 0.5"
MOUNTING
BRACKET
AIRCRAFT FLOOR AIRFRAME STRINGER
MAX. HEIGHT DETAIL
CORRECT GUIDELINE TABLE:
FASTENER SPACING
DIM A
AIRFRAME
STRINGER
AIRCRAFT
FLOOR
MOUNTING
BRACKET
STIFFENER
DIM A DIM B
SCREWS
HARDWARE DIM. A DIM. B
RIVETS
MIN MAX
2*D 4*D
2*D 4*D
4*D - 8*D
4*D - 10*D
NOTE: "D" IS THE DIAMETER OF FASTENER
Figure B-2. General Bracket Design for GTS 8XX
-
GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page C-1
Rev. 2 190-00993-04
Appendix C GTS 8XX Horizontal Mount Details
NO
TE
S:
1.
DIM
EN
SIO
NS
AR
E I
N I
NC
HE
S
2.
DIM
EN
SIO
NS
AR
E F
OR
RE
FE
RE
NC
E O
NL
Y
3.
MO
UN
TIN
G H
OL
E F
OR
8-3
2 P
AN
HE
AD
OR
CA
P S
CR
EW
4.
RE
CO
MM
EN
DE
D S
CR
EW
LE
NG
TH
0.7
5 I
NC
HE
S M
INIM
UM
3
(4X
)
[sgs1]
Figure C-1. GTS 8XX in Horizontal Mount – Center of Gravity
-
Page C-2 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
GMA CONNECTOR
(011-01364-XX)
PARTS VARY DEPENDING ON SPECIFIC KIT
GTS 8XX HORIZONTAL RACK
(115-00784-XX)
GTS 8XX CONNECTOR
(011-01360-XX)
GTS 800 (011-01356-00)
OR
GTS 820 (011-01446-00)
OR
GTS 850 (011-01553-00)
Figure C-2. GTS 8XX Horizontal Mount Outline
-
GTS 8XX AML STC Installation Manual Page C-3
190-00993-04 Rev. 2
STRINGER
SKIN
GTS 8XX UNIT
FABRICATED INSTALLATION
BRACKET
0.50 MAX
Figure C-3. GTS 8XX Horizontal Mount – Attached to Stringers
-
Page C-4 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
1FABRICATED INSTALLATION
BRACKET
SKIN
GTS 8XX UNIT
STRINGER
RIVETS
NAS9301B RIVET (PREFERRED)
MS20470AD4 RIVETS (OPTIONAL)
LENGTH AS APPROPRIATE
DO NOT USE NON-STRUCTURAL HARDWARE TO ATTACH BRACKET TO STRUCTURE
1
Figure C-4. GTS 8XX Horizontal Mount – Stringer Installation
-
GTS 8XX AML STC Installation Manual Page C-5
190-00993-04 Rev. 2
8-3
2 S
CR
EW
(6
X)
11
5-0
07
84
-00
MO
UN
TIN
G T
RA
Y
FA
BR
ICA
TE
D
BR
AC
KE
T
AS
SE
MB
LY
FL
OO
R P
AN
EL
(OR
OT
HE
R A
CC
EP
TA
BL
E
MO
UN
TIN
G S
UR
FA
CE
)
RIV
ET
S (
A/R
)
HA
RD
WA
RE
SP
EC
IFIC
AT
ION
S
SC
RE
WS
WA
SH
ER
S
NU
TS
MS
35
20
6 (
#8
-32
, L
EN
GT
H A
/R);
OR
NA
S6
02
(#
8-3
2 L
EN
GT
H A
/R);
OR
AN
52
5 (
#8
-32
LE
NG
TH
A/R
)
NA
S1
14
9F
N8
32
P (
AN
96
0-8
);
OR
NA
S1
14
9F
N8
16
P (
AN
96
0-8
L)
AN
36
4-8
32
A (
MS
21
08
3N
08
);
OR
MS
21
04
2L
08
OR
NU
TP
LA
TE
S
RIV
ET
S
SE
E N
UT
PL
AT
E T
AB
LE
MS
20
42
6A
D3
-X
MS
20
47
0A
D4
-X;
MS
20
42
6A
D4
-X;
NA
S9
30
1 (
1/8
" D
IA);
OR
NA
S9
30
2 (
1/8
" D
IA)
RIV
ET
S
NO
TE
S:
1.
SE
E H
AR
DW
AR
E T
AB
LE
FO
R O
PT
ION
S
2.
RE
CO
MM
EN
DE
D T
OR
QU
E 1
2-1
5 I
NC
H-L
BS
1
21
NU
TP
LA
TE
TA
BL
E:
NU
TP
LA
TE
DE
SC
RIP
TIO
N
TW
O L
UG
MIN
IAT
UR
ET
WO
LU
G S
TA
ND
AR
DO
NE
LU
G M
INIA
TU
RE
ON
E L
UG
ST
AN
DA
RD
TW
O L
UG
MIN
IAT
UR
E F
LO
AT
ING
TW
O L
UG
ST
AN
DA
RD
FL
OA
TIN
GO
NE
LU
G S
TA
ND
AR
D F
LO
AT
ING
MS
21
069
L0
8
(MK
10
00
-08
)M
S2
10
47
L0
8
(K10
00
-08)
MS
21
071
L0
8
(MK
20
00
-08
)M
S2
10
51
L0
8
(K20
00
-08)
MS
21
07
5L
08
(M
F50
00-0
8)
MS
21
05
9L
08
(F
500
0-0
8)
MS
21
06
1L
08
(F
200
0-0
8)
PA
RT
NU
MB
ER
Figure C-5. GTS 8XX Horizontal Mount – Floor Panel Installation
-
Page C-6 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
HARDWARE SPECIFICATIONS
NOTES:
1. SEE NUTPLATE TABLE FOR OPTIONS
2. SEE HARDWARE TABLE FOR OPTIONS
3. RECOMMENDED TORQUE 12-15 INCH-LBS
4. MINIMUM THICKNESS .063 INCHES, UNLESS ALUMINUM HONEYCOMB CORE PANEL (NO MINIMUM THICKNESS REQUIREMENT)
FABRICATED INSTALLATION
BRACKET
GTS 8XX HORIZONTAL RACK
(115-00784-XX)
8-32 SCREW
6X
(NOT SUPPLIED, 0.75 MIN)
HARDWARE TABLE:
2
4
3
NUTPLATE TABLE:
NUTPLATE
6X1
MS20426AD3-4 RIVET
A/R
FABRICATED INSTALLATION
BRACKET
MS35206 (#8-32, LENGTH A/R)NAS602 (#8-32 LENGTH A/R)AN525 (#8-32 LENGTH A/R)
SCREWS
MS20470AD4-XRIVETSMS20426AD4-XNAS1149FN832P (AN960-8)WASHERSNAS1149FN816P (AN960-8L)AN364-832A (MS21083N08)NUTSMS21042L08
ORNUTPLATES
RIVETS
SEE NUTPLATE TABLE
MS20426AD3-X
MS21069L08 (MK1000-08) MS21047L08 (K1000-08) MS21071L08 (MK2000-08) MS21051L08 (K2000-08) MS21075L08 (MF5000-08) MS21059L08 (F5000-08) MS21061L08 (F2000-08)
PART NUMBERTWO LUG MINIATURE TWO LUG STANDARD ONE LUG MINIATURE ONE LUG STANDARD TWO LUG MINIATURE FLOATING TWO LUG STANDARD FLOATING ONE LUG STANDARD FLOATING
NUTPLATE DESCRIPTION
Figure C-6. GTS 8XX Horizontal Mount – Fabricated Installation Bracket
-
GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page D-1
190-00993-04 Rev. 2
Appendix D GTS 8XX Vertical Mount Details
3.00
CENTER OF GRAVITY
5.80
CENTER OF GRAVITY
6.31
6.94
12.78
3.00
CENTER OF GRAVITY
1.40
CENTER OF GRAVITY
5.80
CENTER OF GRAVITY
1.40
CENTER OF GRAVITY
2.812.00
8.102.39
NOTES:
1. DIMENSIONS ARE IN INCHES
2. DIMENSIONS ARE FOR REFERENCE ONLY
3. MOUNTING HOLE FOR 8-32 PAN HEAD OR CAP SCREW.
4. RECOMMENDED SCREW LENGTH 0.75 INCHES MINIMUM.
3 (4X)
Figure D-1. GTS 8XX Vertical Mount – Center of Gravity
-
Page D-2 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
GTS 800 (011-01356-00)
OR
GTS 820 (011-01446-00)
OR
GTS 850 (011-01553-00)
GTS 8XX CONNECTOR
(011-01360-XX)
GMA CONNECTOR
(011-01364-XX)
PARTS VARY DEPENDING ON SPECIFIC KIT
GTS 8XX VERTICAL RACK
(115-00781-XX)
Figure D-2. GTS 8XX Vertical Mount Installation Drawing
-
GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page D-3
190-00993-04 Rev. 2
GTS 8XX UNIT
EXISTING STRUCTURE
8-32 SCREWS
(4X, MINIMUM)
FABRICATED
MOUNTING PLATE
Figure D-3. GTS 8XX Vertical Mount Example
-
Page D-4 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
NOTES:
1. SEE NUTPLATE TABLE FOR OPTIONS
2. SEE HARDWARE TABLE FOR OPTIONS
3. RECOMMENDED TORQUE 12-15 INCH-LBS
4. MINIMUM THICKNESS .063 INCHES, UNLESS ALUMINUM HONEYCOMB CORE PANEL (NO MINIMUM THICKNESS REQUIREMENT)
MS20426AD3-4 RIVET
A/R
NUTPLATE
6X1
FABRICATED INSTALLATION
BRACKET
FABRICATED INSTALLATION
BRACKET
GTS 8XX VERTICAL RACK
(115-00781-XX)
8-32 SCREW
4X
(NOT SUPPLIED, 0.75 MIN)
4
HARDWARE SPECIFICATIONS
HARDWARE TABLE:
MS35206 (#8-32, LENGTH A/R)NAS602 (#8-32 LENGTH A/R)AN525 (#8-32 LENGTH A/R)
SCREWS
MS20470AD4-XRIVETSMS20426AD4-XNAS1149FN832P (AN960-8)WASHERSNAS1149FN816P (AN960-8L)AN364-832A (MS21083N08)NUTSMS21042L08
ORNUTPLATES
RIVETS
SEE NUTPLATE TABLE
MS20426AD3-X
NUTPLATE TABLE:
MS21069L08 (MK1000-08) MS21047L08 (K1000-08) MS21071L08 (MK2000-08) MS21051L08 (K2000-08) MS21075L08 (MF5000-08) MS21059L08 (F5000-08) MS21061L08 (F2000-08)
PART NUMBERTWO LUG MINIATURE TWO LUG STANDARD ONE LUG MINIATURE ONE LUG STANDARD TWO LUG MINIATURE FLOATING TWO LUG STANDARD FLOATING ONE LUG STANDARD FLOATING
NUTPLATE DESCRIPTION
Figure D-4. GTS 8XX Vertical Mount – Fabricated Installation Bracket
-
GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page D-5
190-00993-04 Rev. 2
HA
RD
WA
RE
SP
EC
IFIC
AT
ION
S
SC
RE
WS
MS
35
20
6 (
#8-3
2, L
EN
GT
H A
/R);
OR
NA
S6
02 (
#8-3
2 L
EN
GT
H A
/R);
OR
AN
525 (
#8-3
2 L
EN
GT
H A
/R)
NA
S1
149
FN
83
2P
(A
N96
0-8
); O
R N
AS
114
9F
N81
6P
(A
N9
60-8
L)
AN
36
4-8
32
A (
MS
210
83N
08
); O
R M
S2104
2L08
MS
20
47
0A
D4-X
; O
R M
S204
26A
D4-X
RIV
ET
S
NO
TE
S:
1.
SE
E H
AR
DW
AR
E T
AB
LE
FO
R O
PT
ION
S
2.
RE
CO
MM
EN
DE
D T
OR
QU
E 1
2-1
5 IN
CH
-LB
S
3.
MIN
IMU
M T
HIC
KN
ES
S .063 IN
CH
ES
, U
NLE
SS
EX
IST
ING
ALU
MIN
UM
HO
NE
YC
OM
B C
OR
E
PA
NE
L
4.
MIN
IMU
M F
OU
R (
4)
8-3
2 F
AS
TE
NE
RS
(O
R L
AR
GE
R)
AT
TA
CH
ING
MO
UN
TIN
G P
LA
TE
OR
BR
AC
KE
T T
O S
TR
UC
TU
RE
HA
RD
WA
RE
TA
BL
E:
8-3
2 S
CR
EW
WA
SH
ER
NU
T
21
WA
SH
ER
S
NU
TS
4
FA
BR
ICA
TE
D
MO
UN
TIN
G P
LA
TE
3
EX
IST
ING
ST
RU
CT
UR
E
8-3
2 S
CR
EW 4X
(NO
T S
UP
PLIE
D, 0.7
5 M
IN)
2
FA
BR
ICA
TE
D
MO
UN
TIN
G P
LA
TE
GT
S 8
XX
MO
UN
TIN
G R
AC
K
GT
S 8
XX
UN
IT
Figure D-5. GTS 8XX Vertical Mount – Attached to Existing Structure
-
Page D-6 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
This page intentionally left blank
-
GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page E-1
190-00993-04 Rev. 2
Appendix E GPA 65 Installation Details
7.50
7.00
1.90
3.80
4.25
0.23 TYP
9.05
0.53
TYP
0.50
0.18
1.00
1.18
1.39
NO
TE
S:
1.
DIM
EN
SIO
NS
AR
E IN
IN
CH
ES
2.
DIM
EN
SIO
NS
AR
E F
OR
RE
FE
RE
NC
E O
NLY
3.
MO
UN
TIN
G H
OLE
FO
R 8
-32 P
AN
HE
AD
OR
CA
P S
CR
EW
.
3
(4X
)
Figure E-1. GPA 65 PA LNA Outline Drawing
-
Page E-2 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
FABRICATED INSTALLATION
BRACKET 4
GPA 65 UNIT
8-32 SCREW
4X
(NOT SUPPLIED)
23
NUTPLATE
6X1
MS20426AD3-4 RIVET
A/R
FABRICATED INSTALLATION
BRACKET
NOTES:
1. SEE NUTPLATE TABLE FOR OPTIONS
2. SEE HARDWARE TABLE FOR OPTIONS
3. RECOMMENDED TORQUE 12-15 INCH-LBS
4. MINIMUM THICKNESS .063 INCHES, UNLESS ALUMINUM HONEYCOMB CORE PANEL (NO MINIMUM THICKNESS REQUIREMENT)
HARDWARE SPECIFICATIONS
HARDWARE TABLE:
NUTPLATE TABLE:
MS35206 (#8-32, LENGTH A/R)NAS602 (#8-32 LENGTH A/R)AN525 (#8-32 LENGTH A/R)
SCREWS
MS20470AD4-XRIVETSMS20426AD4-XNAS1149FN832P (AN960-8)WASHERSNAS1149FN816P (AN960-8L)AN364-832A (MS21083N08)NUTSMS21042L08
ORNUTPLATES
RIVETS
SEE NUTPLATE TABLE
MS20426AD3-X
MS21069L08 (MK1000-08) MS21047L08 (K1000-08) MS21071L08 (MK2000-08) MS21051L08 (K2000-08) MS21075L08 (MF5000-08) MS21059L08 (F5000-08) MS21061L08 (F2000-08)
PART NUMBERTWO LUG MINIATURE TWO LUG STANDARD ONE LUG MINIATURE ONE LUG STANDARD TWO LUG MINIATURE FLOATING TWO LUG STANDARD FLOATING ONE LUG STANDARD FLOATING
NUTPLATE DESCRIPTION
Figure E-2. GPA 65 – Attached to Installation Bracket
-
GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page E-3
190-00993-04 Rev. 2
GPA 65 UNIT
Figure E-3. GPA 65 Mount Example
-
Page E-4 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
8-3
2 S
CR
EW 4X
(NO
T S
UP
PL
IED
)
21
FA
BR
ICA
TE
D I
NS
TA
LL
AT
ION
BR
AC
KE
T3
GP
A 6
5 U
NIT
NOTES:
1.
SE
E H
AR
DW
AR
E T
AB
LE
FO
R O
PT
ION
S
2.
RE
CO
MM
EN
DE
D T
OR
QU
E 1
2-1
5 IN
CH
-LB
S
3.
MIN
IMU
M T
HIC
KN
ES
S .04
0 IN
CH
ES
4.
AP
PR
OP
RIA
TE
RIV
ET
S4
HA
RD
WA
RE
SP
EC
IFIC
AT
ION
S
HA
RD
WA
RE
TA
BL
E:
NU
TP
LA
TE
TA
BL
E:
MS
35
20
6 (
#8
-32
, L
EN
GT
H A
/R)
NA
S6
02
(#
8-3
2 L
EN
GT
H A
/R)
AN
52
5 (
#8
-32
LE
NG
TH
A/R
)
SC
RE
WS
NA
S9
30
1B
-XR
IVE
TS
MS
20
47
0A
D4
-XN
AS
11
49
FN
83
2P
(A
N9
60
-8)
WA
SH
ER
SN
AS
11
49
FN
81
6P
(A
N9
60
-8L
)A
N3
64
-83
2A
(M
S2
10
83
N0
8)
NU
TS
MS
21
04
2L
08
OR
NU
TP
LA
TE
S
RIV
ET
S
SE
E N
UT
PL
AT
E T
AB
LE
MS
20
426
AD
3-X
MS
21
06
9L
08
(M
K1
000
-08
) M
S2
10
47
L0
8
(K1
00
0-0
8)
MS
21
07
1L
08
(M
K2
000
-08
) M
S2
10
51
L0
8
(K2
00
0-0
8)
MS
21
07
5L
08
(M
F5
00
0-0
8)
MS
21
05
9L
08
(F
50
00
-08
) M
S2
10
61
L0
8
(F2
00
0-0
8)
PA
RT
NU
MB
ER
TW
O L
UG
MIN
IAT
UR
E
TW
O L
UG
ST
AN
DA
RD
O
NE
LU
G M
INIA
TU
RE
O
NE
LU
G S
TA
ND
AR
D
TW
O L
UG
MIN
IAT
UR
E F
LO
AT
ING
T
WO
LU
G S
TA
ND
AR
D F
LO
AT
ING
O
NE
LU
G S
TA
ND
AR
D F
LO
AT
ING
NU
TP
LA
TE
DE
SC
RIP
TIO
N
Figure E-4. GPA 65 Example Details
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GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page F-1
190-00993-04 Rev. 2
Appendix F GA 58 Antenna Installation Details
5.63
2.81
2.97
0.55
0.54 4X QMA CONNECTOR
0.34
0.62
2.01
4.03
0.59
0.54
2X 0
2.310
2X 4.620
0.50
2X
0
1.1
3
2X
1.7
60
0.8
80
Ø1.500
1.300
4X Ø0.188
MOUNTING CUTOUT
FORWARD
011-01346-00
GA 58 ANTENNA OUTLINE
011-01346-00
GA 58 ANTENNA OUTLINE
4X 211-60209-16
#8-32 PHP X.75
AS 568A-134
O-RING
AIRCRAFT SKIN
FABRICATE AND INSTALL DOUBLER
PLATE
NOTES:
1. DIMENSIONS: INCHES
2. ANTENNA OUTLINE DIMENSIONS ARE SHOWN FOR REFERENCE
ONLY.
Figure F-1. GA 58 Antenna Outline
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Page F-2 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
2.00 MIN
GA 58 ANTENNA
OUTLINE
NUTPLATES OPTIONAL
Figure F-2. GA 58 Doubler Example
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GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page F-3
190-00993-04 Rev. 2
(5.63)10.04
0.25
8.03
(4.03)
1.000.50
1.00
0.50
Ø1.50
DOUBLER DESIGN GUIDELINES:
DOUBLER
THICKNESS
0.032
# RIVETS
(MINIMUM)
0.040
0.050
0.063
0.070
18
18
18
18
22
SKIN
THICKNESS
0.025
0.032
0.040
0.050
0.063
NOTES:
1. USE 2024-T3 SHEET ALUMINIUM, THICKNESS SPECIFIED IN
TABLE.
2. JOGGLE AS REQUIRED FOR EXISTING STRUCTURE.
3. APPLY CORROSION PROTECTION ON ALL SURFACES OF PART.
• USE CORROSION PROTECTION SPECIFIED IN AIRCRAFT
MAINTENANCE MANUAL, OR
• USE ZINC CHROMATE PRIMER FED STD TT-P-1757, OR
• USE EPOXY PRIMER THAT MEETS MIL-P-23377.
4. DIMENSION MAY VARY DEPENDING ON AIRCRAFT.
5. MINIMUM REQUIRED NUMBER OF RIVETS PER SIDE.
2.31
4.62
2.71
3.39
0.88
1.76
4
4
Ø0.188, 4X
4
4
5
Figure F-3. Antenna Doubler with Joggles Installed on Skin/Fuselage Structure
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Rev. 2 190-00993-04
DOUBLER
MS20426AD3 RIVETS
A/R
NUTPLATES
OPTIONAL
(8-32, 4X)
NOTES:
1. SEE NUTPLATE TABLE FOR OPTIONS
NUTPLATE TABLE:
MS21069L08 (MK1000-08) MS21047L08 (K1000-08) MS21071L08 (MK2000-08) MS21051L08 (K2000-08) MS21075L08 (MF5000-08) MS21059L08 (F5000-08) MS21061L08 (F2000-08)
PART NUMBERTWO LUG MINIATURE TWO LUG STANDARD ONE LUG MINIATURE ONE LUG STANDARD TWO LUG MINIATURE FLOATING TWO LUG STANDARD FLOATING ONE LUG STANDARD FLOATING
NUTPLATE DESCRIPTION
Figure F-4. Isometric View of Joggled Antenna Doubler Assembly
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190-00993-04 Rev. 2
Figure F-5. View of GA 58 Joggled Antenna Doubler from Inside of Fuselage
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Rev. 2 190-00993-04
MS20470AD4
OR
MS20426AD4
RIVETS
(QTY A/R)
8-32 SCREWS
(4X)
GA 58 ANTENNA
(O-RING NOT SHOWN)
FABRICATED DOUBLER
1 2
NOTES:
1. SEE HARDWARE TABLE FOR OPTIONS
2. RECOMMENDED TORQUE 12-15 INCH-LBS
HARDWARE SPECIFICATIONS
HARDWARE TABLE:
NUTPLATE TABLE:
MS35206 (#8-32, LENGTH A/R)NAS602 (#8-32 LENGTH A/R)AN525 (#8-32 LENGTH A/R)
SCREWS
MS20470AD4-XRIVETSMS20426AD4-XNAS1149FN832P (AN960-8)WASHERSNAS1149FN816P (AN960-8L)AN364-832A (MS21083N08)NUTSMS21042L08
ORNUTPLATES
RIVETS
SEE NUTPLATE TABLE
MS20426AD3-X
MS21069L08 (MK1000-08) MS21047L08 (K1000-08) MS21071L08 (MK2000-08) MS21051L08 (K2000-08) MS21075L08 (MF5000-08) MS21059L08 (F5000-08) MS21061L08 (F2000-08)
PART NUMBERTWO LUG MINIATURE TWO LUG STANDARD ONE LUG MINIATURE ONE LUG STANDARD TWO LUG MINIATURE FLOATING TWO LUG STANDARD FLOATING ONE LUG STANDARD FLOATING
NUTPLATE DESCRIPTION
Figure F-6. GA 58 Installation Between Stringers
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190-00993-04 Rev. 2
DOUBLER DESIGN GUIDELINES:
DOUBLER
THICKNESS
0.032
BEND RADIUS
(MIN)
0.040
0.050
0.063
0.070
0.125
0.160
0.200
0.240
0.280
FLANGE
LENGTH (MIN)SKIN
THICKNESS
0.025
0.032
0.040
0.050
0.063
0.38
0.50
0.60
0.72
0.84
FLANGE
LENGTH
Ø1.50
NOTES:
1. USE 2024-T3 SHEET ALUMINIUM, THICKNESS SPECIFIED IN TABLE. USE BEND RADIUS SPECIFIED IN TABLE.
2. APPLY CORROSION PROTECTION ON ALL SURFACES OF PART.• USE CORROSION PROTECTION SPECIFIED IN AIRCRAFT
MAINTENANCE MANUAL, OR• USE ZINC CHROMATE PRIMER FED STD TT-P-1757, OR• USE EPOXY PRIMER THAT MEETS MIL-P-23377.
3. MINIMUM NUMBER OF RIVETS PER SIDE OF THE DOUBLER.
4. DIMENSION MAY VARY DEPENDING ON AIRCRAFT
Ø0.128
A/R
# RIVETS
(MINIMUM)
18
18
18
18
22
Figure F-7. GA 58 Antenna Flanged Doubler Design Detail
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Page F-8 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
NUTPLATES
OPTIONAL
(8-32, 4X)
MS20426AD3 RIVETS
A/R
Figure F-8. Flanged Doubler Assembly with Nutplates
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GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page F-9
190-00993-04 Rev. 2
FUSELAGE SKIN
FABRICATED DOUBLER
MS20470AD4
OR
MS20426AD4
RIVETS
(QTY A/R)
Figure F-9. GA 58 Antenna Flanged Doubler Design Detail
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Page F-10 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation
Rev. 2 190-00993-04
8-32 SCREWS
(4X)
GA 58 ANTENNA
(O-RING NOT SHOWN)
FUSELAGE SKIN
(DOUBLER INSTALLED)
1 2
HARDWARE SPECIFICATIONS
SCREWS
WASHERS
NUTS
MS35206 (#8-32, LENGTH A/R); OR NAS602 (#8-32 LENGTH A/R); OR AN525 (#8-32 LENGTH A/R)
NAS1149FN832 (AN960-8; AN960-8L);
OR NAS1149FN816P
AN364-832A (MS21083N08);
OR MS21042L08
OR
NUTPLATES
RIVETS
SEE NUTPLATE TABLE
MS20426AD3-X
MS20470AD4-X; OR MS20426AD4-XRIVETS
NOTES:
1. SEE HARDWARE TABLE FOR OPTIONS
2. RECOMMENDED TORQUE 12-15 INCH-LBS
NUTPLATE TABLE:
PART NUMBER NUTPLATE DESCRIPTION
TWO LUG MINIATURETWO LUG STANDARDONE LUG MINIATUREONE LUG STANDARDTWO LUG MINIATURE FLOATINGTWO LUG STANDARD FLOATINGONE LUG STANDARD FLOATING
MS21069L08 (MK1000-08)MS21047L08 (K1000-08)
MS21071L08 (MK2000-08)MS21051L08 (K2000-08)
MS21075L08 (MF5000-08)MS21059L08 (F5000-08)MS21061L08 (F2000-08)
Figure F-10. GA 58 Antenna Installation on Flanged Doubler
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GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page F-11
190-00993-04 Rev. 2
Figure F-11. View of GA 58 Antenna Installation
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Rev. 2 190-00993-04
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