gts 8xx aml stc installation manual part 2 mechanical...

190-00993-04 November 2009 Rev. 2

GTS 8XX

AML STC Installation Manual

Part 2

Mechanical Installation

GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page A

Rev. 2 190-00993-04

© 2009

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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.

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-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.



F-1 Appendix F Updated Figure F-1.






2


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

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

Page ii GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation

190-00993-04 Rev. 2

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

GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page 1-1

190-00993-04 Rev. 2

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.

2 GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation

Rev. 2 190-00993-04

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Rev. 2 190-00993-04

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.



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


FACING FORE OR AFT ON A VERTICAL

SURFACE



FACING UP OR DOWN ON A VERTICAL

SURFACE

Figure 2-2. GTS 8XX Horizontal Mount on a Vertical Surface


Rev. 2 190-00993-04

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


VERTICAL RACK WITH CONNECTOR

FACING FORE OR AFT ON A HORIZONTAL

SURFACE.

UP

SIDEFWD


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


190-00993-04 Rev. 2

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.


Rev. 2 190-00993-04

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.


190-00993-04 Rev. 2

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



TO ONE SIDE ON A

HORIZONTAL SURFACE



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.


Rev. 2 190-00993-04

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.


190-00993-04 Rev. 2

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.


Rev. 2 190-00993-04

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

GTS 8XX AML STC Installation Manual - Part 2 - Mechanical Installation Page A-1

Rev. 2 190-00993-04

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


(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


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


(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


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


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


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


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)


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


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


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


Rev. 2 190-00993-04

NOTES:





MS20426AD3-4 RIVET

A/R

NUTPLATE

6X1


BRACKET


BRACKET

GTS 8XX VERTICAL RACK

(115-00781-XX)

8-32 SCREW

4X

(NOT SUPPLIED, 0.75 MIN)

4


HARDWARE TABLE:


SCREWS


ORNUTPLATES

RIVETS

SEE NUTPLATE TABLE

MS20426AD3-X

NUTPLATE TABLE:




Figure D-4. GTS 8XX Vertical Mount – Fabricated Installation Bracket


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


Rev. 2 190-00993-04


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


BRACKET 4

GPA 65 UNIT

8-32 SCREW

4X

(NOT SUPPLIED)

23

NUTPLATE

6X1

MS20426AD3-4 RIVET

A/R


BRACKET

NOTES:






HARDWARE TABLE:

NUTPLATE TABLE:


SCREWS


ORNUTPLATES

RIVETS

SEE NUTPLATE TABLE

MS20426AD3-X




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

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

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


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


Rev. 2 190-00993-04

DOUBLER

MS20426AD3 RIVETS

A/R

NUTPLATES

OPTIONAL

(8-32, 4X)

NOTES:


NUTPLATE TABLE:




Figure F-4. Isometric View of Joggled Antenna Doubler Assembly


190-00993-04 Rev. 2

Figure F-5. View of GA 58 Joggled Antenna Doubler from Inside of Fuselage


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:




HARDWARE TABLE:

NUTPLATE TABLE:


SCREWS


ORNUTPLATES

RIVETS

SEE NUTPLATE TABLE

MS20426AD3-X




Figure F-6. GA 58 Installation Between Stringers


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


Rev. 2 190-00993-04

NUTPLATES

OPTIONAL

(8-32, 4X)

MS20426AD3 RIVETS

A/R

Figure F-8. Flanged Doubler Assembly with Nutplates


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


Rev. 2 190-00993-04

8-32 SCREWS

(4X)

GA 58 ANTENNA

(O-RING NOT SHOWN)

FUSELAGE SKIN

(DOUBLER INSTALLED)

1 2


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:



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


190-00993-04 Rev. 2

Figure F-11. View of GA 58 Antenna Installation


Rev. 2 190-00993-04


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