BendixKing Avionics AutoPilots Transponders - FreeFlight … · 2020. 5. 6. · Capstone-II-0103 FreeFlight Systems 3700 Interstate 35 S Waco, TX 76706 This document contains FreeFlight

Publication Number D201411000017, Revision 1 Page T-1

5 February 2016

© Honeywell International Inc. Do not copy without express permission of Honeywell.

FreeFlight Systems AML STC

KGX 130/150

STC Number SA02426AK

Legal Notice Export Control

This document contains technical data and is subject to U.S. export regulations. These commodities, technology, or software were exported from the United States in accordance with the export administration regulations. Diversion

contrary to U.S. law is prohibited. ECCN: 7E994.

9201-B San Mateo Blvd N.E.

Albuquerque, New Mexico 87113 U.S.A.

CAGE: 6PC31

Telephone: 855-250-7027 (Toll Free U.S.A./Canada) Telephone: 505-903-6148 (International Direct) Website: www.BendixKing.com/support

The attached documents are distributed by BendixKing to provide technical support for installation of the BendixKing KGX 130/150 using the FreeFlight Systems AML STC Number SA02426AK.

Publication Number D201411000017, Revision 1 Page T-2

5 February 2016

© Honeywell International Inc. Do not copy without express permission of Honeywell.

DOCUMENT REVISIONS

Revision Description of Change DATE

(-) Initial release Nov 10, 2014

1 Adding GPS position source capability with Garmin 430W/530W

Documents updated: QPL-0103 Rev B, II-0103 Rev H, AFMS-0103 Rev E, CS-0103-WD Rev D, ICA-0103 Rev C

Feb 5, 2016

FREE FLIGHT SYSTEMS

Document Number: MPF/PM-2014-011

8150 Springwood Drive, Suite 100 Irving, TX 75073

817-899-7044 Fax 972-830-9419

e-mail: [email protected]

Date: 24 Oct 2014

FreeFlight Systems Authorization to Distribute STC SA02426AK

Dear Mr. Shears,

In accordance with AC 2L-40A Guide for Obtaining a Supplemental Type Certificate (STC), FreeFlight Systems (FFS) hereby authorizes Bendix-King to distribute STC SA02426AK to their dealer network and customers in support of modifying aircraft listed within the approved within the STC. As mutually agreed too between FreeFlight Systems and Bendix-King, FreeFlight Systems will provide all STC updates, revisions, Service Bulletins, and Airworthiness Directives directly to Bendix-King who will in turn be responsible for providing those documents and information to their dealer network and customers.

If you require any further information or have any questions please contact the undersigned.

Best regards,

Michael P Frazier Director of Product and Program Management FreeFlight Systems

Report No. CAPSTONE-QPL-0103 Rev B Page 1 of 4

QUALIFIED PARTS LIST / MATRIX

For

ADS-B Out System

On

APPROVED MODEL LIST for ADS-B OUT SYSTEM

Installed in Approved Model List Aircraft Report No. Capstone-AML-1013

Report No. CAPSTONE-QPL-0103

Prepared by: M. Frazier

Approved by: J. Johnston

____________________________________________________________________________________________


RECORD OF REVISIONS

REV BY

APPROVAL

DATE

REVISIONS AND/OR ADDITIONS

IR

RDH

RDH 3-27-13 Initial Release

A MPF JJ 9-04-14 Updated FDL-978 Part Numbers to reflect TSO PN Change Added Part Number Equivalency for Customer rebranded systems Section C

B MPF JJ 06-08-2015 Removed Sections A and B. Renamed

section C to A. Corrected TC-978 Part number.

____________________________________________________________________________________________


TABLE OF CONTENTS

RECORD OF REVISIONS………...…………………………………….. 2

TABLE OF CONTENTS ….…………………………………………….. 3

SECTION A – MODELS …….………………………………………….. 4

SECTION B – PARTS ………….……………………………………….. 4

SECTION C – PART NUMBER EQUIVALENCY …………………….. 4

____________________________________________________________________________________________


SECTION A – PART NUMBER EQUIVALENCY

FreeFlight Systems sells the FDL-978 series ADS-B Transceivers and Receivers to other avionics manufacturers, rebranded as their own product. The following tables provide cross-reference the FreeFlight model name and part number to the equivalent rebranded product model name and part number. Anywhere the FreeFlight Systems Part Number or Model Number is used within this document or the associated Supplemental Type Certificate, the equivalent Rebranded Part Number identified in the following tables is authorized.

Bendix-King Avionics:

FreeFlight Systems Model

Name FreeFlight New P/N

FreeFlight Customer P/N

Bendix King Model Name

Bendix King Part Number

FDL-978-XVR no GPS

87098-10-FX10 = 87098-10-BX10 KGX 130 Transceiver (No GPS) Single Band

89000016-130

FDL-978-XVR with internal GPS

87098-00-FX00 = 87098-00-BX00 KGX 150 Transceiver (With Internal GPS) Single Band

89000016-151

FDL-978-RX no GPS 87098-10-FR10 = 87098-10-BR10 KGX 130 Receiver (No GPS) Single Band

89000016-131

FDL-978-RX with internal GPS

87098-00-FR00 = 87098-00-BR00 KGX 150 Receiver (With Internal GPS) Single Band

89000016-150

TC978 Control Head 87349 = 87349 KGX Control Panel 89000016-001

Aspen Avionics:

FreeFlight Systems Model Name

FreeFlight New P/N

FreeFlight Customer P/N

Aspen Avionics Model Name

Aspen Part Number

FDL-978-XVR no GPS

87098-10-FX10 = 87098-10-AX10 ATX100 910-00019-001

FDL-978-XVR with internal GPS

87098-00-FX00 = 87098-00-AX00 ATX100G 910-00020-001

Capstone-II-0103

FreeFlight Systems

3700 Interstate 35 S

Waco, TX 76706

This document contains FreeFlight Systems proprietary and confidential information. It is loaned for limited purposes only and remains the

property of FreeFlight Systems. It may not be reproduced in whole or in part without written consent of FreeFlight Systems and must not be

disclosed to persons not having need of such disclosure consistent with the purpose of the loan. The document is to be returned to FreeFlight Systems upon request and/or upon completion of the use for which it was loaned.

Rev H Page 1 of 48

INSTALLATION INSTRUCTIONS

For

APPROVED MODEL LIST

for ADS-B SYSTEM

Installed in Approved Model List Aircraft

Report No. Capstone-II-0103

Prepared by: J. Johnston

Approved by: M. Frazier

Capstone-II-0103

FreeFlight Systems proprietary Rev. H Page 2 of 53

Record of Revisions

REV BY APPROVAL DATE REVISIONS AND/OR ADDITIONS

IR RDH RDH 10-28-12 INITIAL RELEASE

A RDH RDH 09-09-13 Corrections indicated by change bar

B RDH RDH 11-20-13 Added table of acceptable aircraft installation configurations,

information on composite aircraft antenna installations,

information on pressurized aircraft antenna installations and

other items marked by change bar.

C RDH RDH 02-10-14 Updated for FAA comments

D JAJ MF 06-23-14 Added warning language and placard installation instructions

for installations with MX-20 MFD’s.

E MPF JAJ 07-31-14 Removed Rev D changes

Modified Part Numbers to new TSO

Added Part Number Equivalency

Changed FDL-978-XVR to higher level FDL-978 to reflect

new configurations

Added FDL-978-RX Information

Remove Merrill Field Information

F JAJ MPF 09-18-14 Corrected installation configuration table. Reclassified some

required equipment to as needed per installation. Restated

Electrical Load Analysis criteria. Restated several items to

refer only to newly installed ADS-B system related

equipment.

G JAJ MPF 2-19-15 Add Aspen EFD 1000/ EFD 500 Display compatibility.

Separated out MFD configuration instructions – Section 2.11.

Added QCR replacement checkout procedure – Section 8.4,

Moved “ADS-B Out Only” column in config table to note.

Removed Aspen EFD out of controller for GDL-90 column.

Add note that transponder control is preferred. Change

wording for TSO install manual rev to “current revision”.

Correct cover page. Add N/A as appropriate to config table.

H JAJ MPF 6-8-15 Updated revision tracking tables. Added SL-70R to Section

3.1 Pre-Installation Considerations for single-point of entry.

Updated nomenclature from FDL-978-XVR to FDL-

978. Corrected FDL-978-XVR description. Improved

References list. Added Acronyms Added Garmin

400W/500W position source integration and transmitter and

transceiver “Lite” variants with limited connectivity.

Capstone-II-0103


Corrected Approved Configurations table to include the SL-

70R (remote) transponder. Added Permitted software

versions. Added the approved Garmin devices for

integration. Corrected Status LEDs table. Clarified

single antenna installation statement. Corrected VSWR

requirement in 2.5.5.1 Caution. Described Time Mark

Input / Output. Corrected the “Controller for single

point of entry” transponder list to match the previously

approved wiring diagram. Refined TSO manual

references. Added required configurations table when a

Garmin Position Source is used. Removed section 8.4

“QCR Replacement Checkout (Previous Installation)”. Added Section 11, “Documentation Required After

Installation Completion”

Capstone-II-0103


List of Effective Pages

LIST OF REVISIONS REV

-

A

B

C

D

E

F

G

H

LIST OF EFFECTIVE PAGES

For incremental changes each revised page will have (-X) following current revision (E.g. A-1, A-2) until

entire document is revised to the next letter level. Current page revision will be reflected in the table

below at each change. In addition:

Changes made to a line will be indicated by a vertical bar in the left margin next to the line.

Changes made to a paragraph should be indicated by a vertical bar in the left margin next to the

paragraph letter or number.

Changes made to a complete page should be indicated by a vertical bar to the right of the page

number.

TITLE/SECTION

Revised

PAGES REV NO.

Manual-All All -

Manual-All All A

Manual-All

All B

Manual-All

All C

1.2 Reason, 4.10 MX-20

Placard Installation

8, 30 D

Manual-All

All E

Manual-All

All F

Configuration Matrix Table,

Section 2.11 CDTI,

QCR Replacement checkout

procedure

1, 7, 24, 40-41 G

Manual-All All H

TITLE/SECTION

Revised

PAGES REV NO.

Manual-All All H

Capstone-II-0103


Table of Contents:

Record of Revisions .............................................................................................................2 List of Effective Pages .........................................................................................................4 Table of Contents: ................................................................................................................5

1 Planning Information ...............................................................................................8 1.1 Effective Aircraft ............................................................................................................ 8 1.2 Reason ............................................................................................................................. 9 1.3 Equipment Description ................................................................................................... 9

1.3.1 FDL-978 Universal Access Transceiver Configurations ............................................ 9 1.3.2 Part Number Equivalency ......................................................................................... 12

1.4 System Interfaces .......................................................................................................... 12 1.4.1 Multi-Function Display ............................................................................................. 12 1.4.2 Altitude Encoder ....................................................................................................... 12

1.4.3 Control Panel ............................................................................................................ 12 1.4.4 Annunciator Output .................................................................................................. 12 1.4.5 External GPS/WAAS Sensor Interface ..................................................................... 12 1.4.6 Maintenance Interface ............................................................................................... 12

1.5 Antenna Requirements (Ref CS-0103-ANT drawing) ................................................. 13 1.5.1 UAT Antennas .......................................................................................................... 13 1.5.2 GPS Antennas for FreeFlight GPS/WAAS............................................................... 13

1.6 Test Equipment ............................................................................................................. 13 1.6.1 Required Test Equipment ......................................................................................... 13 1.6.2 Required Test Equipment for Certain Installations .................................................. 13

1.7 Weight and Balance ...................................................................................................... 14 1.8 Electrical Load .............................................................................................................. 14 1.9 References ..................................................................................................................... 15

1.10 Project Data List ........................................................................................................... 15 1.11 Definitions and Acronyms ............................................................................................ 16

2 Installation..............................................................................................................17 2.1 Pre-Installation Information .......................................................................................... 17 2.2 Installation Overview .................................................................................................... 17 2.3 Material Required But Not Supplied ............................................................................ 17 2.4 Special Tools Required ................................................................................................. 17

2.5 Equipment Mounting .................................................................................................... 18 2.5.1 Cabling and Wiring ................................................................................................... 18 2.5.2 FDL-978 Series Mounting ........................................................................................ 18 2.5.3 Antenna Installation and Connections ...................................................................... 19 2.5.4 GPS Antenna for a FreeFlight GPS installation ....................................................... 19

2.5.5 UAT Antennas ........................................................................................................... 21

2.5.6 UAT Antenna Ground Plane ..................................................................................... 22

2.5.7 UAT Antenna Cable ................................................................................................. 22 2.6 Optional Installation Kits .............................................................................................. 23 2.7 Equipment Required Per Aircraft ................................................................................. 23 2.8 Approved Optional Equipment ..................................................................................... 24

2.8.1 Optional Altitude Digitizer Adapter Plates ............................................................... 25 2.9 Reserved ........................................................................................................................ 25

Capstone-II-0103


2.10 Personality Module (PM) .............................................................................................. 25 2.11 CDTI (Multifunction Display) ...................................................................................... 26 2.12 Status LEDs .................................................................................................................. 26 2.13 Discrete Inputs .............................................................................................................. 26

2.13.1 Air/Ground Input .................................................................................................. 26 2.13.2 Traffic Test Input .................................................................................................. 27

2.14 Discrete Outputs............................................................................................................ 27 2.14.1 ADS-B Status Output ............................................................................................ 27 2.14.2 TX Suppression Output......................................................................................... 27

2.15 Time Mark Input / Output ............................................................................................. 27 3 Accomplishment Instructions – General Notes, Access & Figures .......................28

3.1 Pre-installation Considerations ..................................................................................... 28 4 Accomplishment Instructions – Mechanical ..........................................................31

4.1 General Guidelines: ...................................................................................................... 31 4.2 Composite Structure Antenna Installation General Guidelines: ................................... 31 4.3 Pressurized Structure Antenna Installation General Guidelines: .................................. 32 4.4 GPS Antenna Mechanical Installation .......................................................................... 32 4.5 Upper L-Band Antenna Mechanical Installation .......................................................... 32 4.6 Lower L-Band Antenna Mechanical Installation .......................................................... 32 4.7 Optional Altitude Digitizer Mechanical Installation ..................................................... 32 4.8 ADS-B Control Panel Mechanical Installation ............................................................. 33 4.9 ADS-B Equipment Mechanical Installation ................................................................. 33

5 Accomplishment Instructions – Electrical .............................................................34 5.1 FDL-978 Series Wiring Installation.............................................................................. 34 5.2 Wiring diagram & Equip Installation on Equip Shelf Assy ......................................... 34 5.3 Main Wiring Diagram Installation ................................................................................ 34

5.3.1 Aircraft Power Wiring Installation ........................................................................... 35 5.3.2 FDL-978 Series Control Wiring Installation ............................................................ 35 5.3.3 TC978 Controller Wiring Installation ....................................................................... 35 5.3.4 FTM-190C Transponder Monitor Wiring Installation .............................................. 35 5.3.5 WI-FI Wiring Installation ......................................................................................... 35 5.3.6 GPS/WAAS 1201 Wiring Installation ...................................................................... 35 5.3.7 Air/Ground Discrete Wiring Installation .................................................................. 35 5.3.8 L-Band Suppression Wiring Installation .................................................................. 36

5.3.9 ADS-B Status Annunciator ....................................................................................... 36 5.3.10 FDL-978-XVR ARINC 429 Wiring Installation .................................................. 36 5.3.11 FDL-978-Series RF Cable Terminations (Ref Fig 1) ........................................... 36

5.4 Circuit Breaker Panel Modification .............................................................................. 37 5.5 Optional Altitude Digitizer Electrical Installation ........................................................ 37

5.6 Altitude Reporting Equipment Interface ....................................................................... 37 5.7 System Continuity and Isolation Test ........................................................................... 37

6 Installation Outline for GDL-90 Replacement ......................................................38 6.1 Assemble the QCR for GDL-90 Replacement.............................................................. 38 6.2 GDL-90 Replacement – Quick Change Rack (QCR) ................................................... 38 6.3 Installation without QCR .............................................................................................. 40 6.4 Configuration with TC-978........................................................................................... 41

Capstone-II-0103


7 Preservation of Previous Systems ..........................................................................41 8 Equipment Operational/Functional Test .................................................................42

8.1 Preliminary Checkout ................................................................................................... 42 8.2 Installation Setup and Configuration ............................................................................ 42

8.2.1 System Checkout – Power on Self-Test (POST) ...................................................... 43 8.3 FT-9000 Ramp Tester Initial Installation Checkout ..................................................... 43

8.3.1 RCEP Post Installation Procedure ............................................................................ 43 9 GPS / VHF Comm Interference Check ..................................................................45 10 Construction & Validation of Structures ................................................................46 11 Documentation Required After Installation Completion .......................................48

11.1 Instructions for Continued Airworthiness Modification for any Interfacing Component

48 11.2 Instructions for Continued Airworthiness Modification If an External (non-FreeFlight)

GPS is Used as a Position Source ............................................................................................. 48 11.3 Instructions for Continued Airworthiness Completion Instructions ............................. 48 11.4 Airplane Flight Manual Supplement Completion Instructions ..................................... 49

Capstone-II-0103


1 Planning Information

1.1 Effective Aircraft

For specific Aircraft Models Listed refer to FreeFlight Systems Report No: Capstone-AML-0103

Approved Model List for ADS-B System Installed in Approved Model List Aircraft.

Acceptable aircraft configurations based on previously installed equipment (Current

Configurations)

Table 1-1: Approved Configurations

Equipment currently in the aircraft before UAT Installation: New Equipment Installed(8)

Transponder Type: Controller for

4096 Code into GDL-90(5)

MFD FDL-978 External

Transponder Monitor(7)

TC-978 Control Head

Wi-Fi Module

None (Configuration 1)

MX-20, GMX-200 MX-20, GMX-200 Yes N/A Optional

Optional GSL-71 Chelton(4) Yes N/A Optional

None Any Yes N/A Yes

Any None Yes N/A Yes

KT-71, KT-76, KT-76A, KT-76C, KT-79, RT359A, GTX-320A,

TDR90, TDR-950, Narco 165, KXP-756

(Configuration 2)

MX-20, GMX-200 MX-20, GMX-200 Yes * * Optional(7) Yes

Optional

GSL-71 Chelton(4) Yes * * Optional(7) Yes

N/A EFD1000(1)(3),

EFD500(1) Yes * * Optional(7) No (1)(2)

Any None Yes * * Optional(7) Yes

SL-70, SL-70R, GTX-32, GTX327, GTX-33, GTX330, GTX-

330 ES (Configuration 3)

MX-20, GMX-200,EFD1000(1)(2)

MX-20, GMX-200,EFD1000(1)(3),

EFD500(1)(3) Yes N/A No

Optional

GSL-71 Chelton(4) Yes N/A No

Transponder (preferred)

MX-20, GMX-200,EFD1000(1)(3),

EFD500(1)(3) Yes N/A No

Any None Yes N/A Yes(6) (or optional

separate annunciator light)

*NOTE: If FDL-978 with internal transponder monitor is installed remote transponder monitor not required. (1) Note: Aspen Avionics EFD-1000 and EFD-500 require Software Version MAP ver. 2.7.2 IOP: 2.0.5 or subsequent FAA approved software for

approved compatible integration. (2) Note: Aspen Avionics EFD-1000 properly configured as a Primary Flight Display is required to input mode 3A 4096 code into the UAT when necessary with configuration 2. (3) Note: Aspen Avionics EFD-1000 properly configured as a Primary Flight Display (PFD) or Multifunction Flight Display (MFD) or an EFD-

500 can display ADS-B-in data. (4) Note: Chelton refers to the Chelton FlightLogic model MFD. (5) Note: Refer to FAA document AC 20-165A or later for further ADS-B out guidance. (6) Note: Transponder control is preferred for single point of entry for Squawk and Ident. (7) Note: The external transponder monitor is no longer being produced since all FDL-978 units are equipped with the internal transponder

monitoring function. (8) Note: The FDL-978 system may be installed in an “ADS-B Out-only” configuration while maintaining rule compliance, since “ADS-B in” is not required. Without “ADS-B in”, no traffic or weather will be displayed.

Capstone-II-0103


1.2 Reason

To equip the aircraft with an FreeFlight System Universal Access Transceiver Automatic

Dependent Surveillance – Broadcast Class B/B1 System, to add the functionality of ADS-B out-in

or ADS-B out only based on installed display equipment (configuration determines operational

capability) to the aircraft. These Installation Instructions direct the installation and activation of the

FreeFlight FDL-978 Series UAT System.

Limitation: These STC approved installation Instructions do not include authorization for

installation new air data, pressure altitude sensors, GPS, multifunction displays or other ADS-B

supporting systems. These “existing” systems shall be previously installed / FAA approved or will

be installed and FAA certified appropriately prior to interface with new ADS-B system covered by

these installation instructions.

Limitation: This STC shall not be installed in an aircraft with existing 8.33 KHz spacing VHF

transceiver(s) unless additional frequency EMI immunity testing is accomplished as specified in

Capstone-GTP-0103 test procedure. This additional EMI testing shall be as specified and agreed

with/coordinated through ACO.

If an 8.33 KHz spacing transceiver(s) are to be installed after installation of this STC the above

testing and coordination with ACO is required before installation of transceivers and aircraft return

to service.

Limitation: When installing this STC on an aircraft equipped with a Chelton Flight Systems

MFD: The Chelton Flight Systems Multifunction Display (MFD) was developed with Collision

Situational Awareness (CSA) with Collision Detection (CD). This presents a limitation when

integrated with the FDL-978, as the FDL-978 does not provide CD or CSA because those

functions are non-standard. In order to prevent the display of the “AUX SENSOR” yellow flag

that will mask other warnings, the FDL-978 indicates that CSA is available in the Heartbeat

message. Therefore, the Chelton Flight Systems MFD display indicates that the CSA function is

available, when it is not. This does not affect another functions or avionics. The required warnings

for ADS-B Failure and ADS-B GPS Failure are annunciated normally.

1.3 Equipment Description

1.3.1 FDL-978 Universal Access Transceiver Configurations

The FreeFlight FDL-978 UAT system is available in four (4) configurations:

FDL-978-XVR 978MHz ADS-B Transceiver (ADS-B IN and OUT)

FDL-978-XVRL Transceiver with internal WAAS/GPS sensor (ADS-B IN and OUT)

FDL-978-RX 978MHz ADS Receive only (ADS-B IN)

FDL-978-TXL Transmitter with internal WAAS/GPS sensor (ADS-B OUT)

Where applicable to all configurations, the term FDL-978 will be utilized. When an item is

specific to the one configuration, the complete Model Identifier shall be used.

All FDL-978 systems are identical with regard to size, weight, and power.

1.3.1.1 FDL-978-XVR Description

The FreeFlight FDL-978-XVR is a remote mounted product that contains a Universal Access

Transceiver. It is available in two configurations (P/N 87098-00-FX00) which contain a

GPS/WAAS receiver and (P/N 87098-10-FX10) which requires an approved external GPS/WAAS

Sensor. The FDL-978-XVR will transmit own ship data via the UAT data link. It will receive data

Capstone-II-0103


from other UAT equipped aircraft, as well as FIS-B weather – the received data may be output to

an appropriate display if so configured. This modification will install one (1) each FDL-978-XVR

UAT P/N 87098-00-FX00 with internal GPS sensor; or one (1) each FDL-978-XVR UAT P/N

87098-10-FX10 without internal GPS sensor (and circuit breaker), and one (1) each approved

GPS/WAAS Sensor such as the 1201 GPS/WAAS Sensor part number 84100-03-0304 in the

aircraft. Install 1 each circuit breaker if the aircraft is not equipped with an existing 1201

GPS/WAAS Sensor. Install 1 each FTM-190C Transponder Monitor part number 86930-00-101A

(or P/N 87098-00-FX00 XVR with internal transponder monitor function), when required in the

aircraft. Install 1 each Altitude Digitizer part number SSD120-(XX)N(X), and 1 each circuit

breaker when the optional Altitude Digitizer is installed. Install 1 each TC-978 Controller in the

cockpit when required. Install 1 each GPS Antenna on the top of the aircraft fuselage. Install 1

each UAT antenna for single-antenna installation or install 2 each UAT antennas for diversity

installations.

1.3.1.2 Features

The features of the FDL-978-XVR UAT Transceiver include:

10-40 VDC power capability.

978 MHz Universal Access Transceiver data link radio designed to support ADS-B, TIS-B

and FIS-B airborne and ground applications.

GPS/WAAS receiver (XVR P/N 87098-00-FX00) with an internal GPS/WAAS receiver and

(XVR P/N 87098-10-FX10) which requires an external GPS/WAAS receiver such as the

1201 GPS/WAAS receiver for state of the art fast, accurate ADS-B position data (12-

channel parallel tracking, that determines position and integrity data). Provides integrity data

through the use of Fault Detection and Exclusion (FDE). Supports oceanic and both foreign

and domestic en route, terminal, non-precision approach, and departure operations.

Interface to an Altitude Encoder or ADC via RS-232 or ARINC 429 buses.

Interface to a Control Panel or Transponder via RS-232 bus.

Interface to a Garmin MX20 or a GMX200 Multi-function Display, the Garmin GNS 400-

and 500-series displays, and other display units that support the Garmin or Public ICD

standard.

1.3.1.3 FDL-978-XVRL Description

The FreeFlight FDL-978-XVRL is a remote mounted product that contains a Universal Access

Transceiver. It is available in one configurations (P/N 87098-00-FX0L) which contains a

GPS/WAAS receiver. The FDL-978-XVRL will transmit own ship data via the UAT data link. It

will receive data from other UAT equipped aircraft, as well as FIS-B weather – the received data

may be output to a Wi-Fi Module if so configured. This modification will install one (1) each

FDL-978-XVRL UAT P/N 87098-00-FX0L with internal GPS sensor, Install 1 each Altitude

Digitizer part number SSD120-(XX)N(X), and 1 each circuit breaker when the optional Altitude

Digitizer is installed. Install 1 each TC-978 Controller in the cockpit. Install 1 each GPS Antenna

on the top of the aircraft fuselage.

1.3.1.4 Features

The features of the FDL-978-XVRL UAT Transceiver include:


978 MHz Universal Access Transceiver data link radio designed to support ADS-B, TIS-B

and FIS-B airborne and ground applications.

GPS/WAAS receiver with an internal GPS/WAAS receiver. Provides integrity data through

the use of Fault Detection and Exclusion (FDE).

Capstone-II-0103


Interface to an Altitude Encoder via RS-232

Interface to a Transponder via RS-232 bus

Interface to the FreeFlight Wi-Fi module for ADS-B IN data.

1.3.1.5 FDL-978-RX Description

The FreeFlight FDL-978-RX is a remote mounted product that contains a 978MHz ADS-B

receiver. The FDL-978-RX is identical to the FDL-978-XVR in all respects except the Transmit

function has been disabled.

The FDL-978-RX is available in two configurations (P/N 87098-00-FR00) which contain a

GPS/WAAS receiver and (P/N 87098-10-FR10) which requires an external GPS/WAAS sensor

such as the GPS/WAAS 1201 Sensor. It will receive data from other ADS-B equipped aircraft, as

well as FIS-B weather – the received data may be output to an appropriate display if so configured.

This modification will install one (1) each FDL-978-RX P/N 87098-00-FR00 with internal GPS

sensor; or one (1) each FDL-978-RX UAT P/N 87098-10-FR10 without internal GPS sensor (and

circuit breaker), and one (1) each GPS WAAS Sensor such as the 1201 GPS/WAAS Sensor part

number 84100-03-0304 in the aircraft. Install 1 each circuit breaker if the aircraft is not equipped

with an existing 1201 GPS/WAAS Sensor. Install 1 each FTM-190C Transponder Monitor part

number 86930-00-101A (or P/N 87098-00-FR00 RX with internal transponder monitor function),

when required in the aircraft. Install 1 each Altitude Digitizer part number SSD120-(XX)N(X),

and 1 each circuit breaker when the optional Altitude Digitizer is installed. Install 1 each GPS

Antenna on the top of the aircraft fuselage.

1.3.1.6 Features

The features of the FDL-978-RX UAT Receiver include:


978 MHz UAT Receiver data link radio designed to support ADS-B, TIS-B and FIS-B

airborne and ground applications.

GPS/WAAS receiver (RX P/N 87098-00-FR00) with an internal GPS/WAAS receiver and

(RX P/N 87098-10-FR10) which requires an external GPS/WAAS sensor such as the 1201

GPS/WAAS receiver for state of the art fast, accurate ADS-B position data (12-channel

parallel tracking, that determines position and integrity data). Provides integrity data through

the use of Fault Detection and Exclusion (FDE). Supports oceanic and both foreign and

domestic en route, terminal, non-precision approach, and departure operations.

Interface to an Altitude Encoder via RS-232 or ARINC 429 buses.

Interface to a Control Panel or Transponder via RS-232 bus.

Interface to a Garmin MX20 or a GMX200 Multi-function Display, the Garmin GNS 400-

and 500-series displays, and other display units that support the Garmin or Public ICD

standard.

1.3.1.7 FDL-978-TXL Description

The FreeFlight FDL-978-TXL is a remote mounted product that contains a Universal Access

Transmitter. It is available in one configuration (P/N 87098-00-FT0L) which contain a

GPS/WAAS receiver The FDL-978-TXL will transmit own ship data via the UAT data link. This

modification will install one (1) each FDL-978-TXL UAT P/N 87098-00-FT0L with internal GPS

sensor. Install 1 each Altitude Digitizer part number SSD120-(XX)N(X), and 1 each circuit

breaker when the optional Altitude Digitizer is installed. Install 1 each TC-978 Controller or other

approved controller in the cockpit when required. Install 1 each GPS Antenna on the top of the

aircraft fuselage.

Capstone-II-0103


1.3.1.8 Features

The features of the FDL-978-TXL UAT Transmitter include:


978 MHz Universal Access Transmitter designed to support ADS-B OUT airborne and

ground applications.

GPS/WAAS receiver with an internal GPS/WAAS receiver provides integrity data through

the use of Fault Detection and Exclusion (FDE).

Interface to an Altitude Encoder via RS-232

Interface to a Transponder via RS-232 bus

1.3.2 Part Number Equivalency

FreeFlight Systems sells the FDL-978 series ADS-B Transceivers and Receivers and other parts

associated with this STC to other avionics manufacturers, rebranded as their own product. Refer

to Capstone-QPL-0103 for Part Number cross-reference.

1.4 System Interfaces

The interfaces for a typical FDL-978 installation are listed below:

1.4.1 Multi-Function Display

The FDL-978 Series can provide own ship, traffic, and FIS-B data through an RS-232/RS-422

serial port and/or ARINC 429 port.

1.4.2 Altitude Encoder

The FDL-978 Series can interface with a transponder or an altitude encoder to obtain pressure

altitude data via an RS-232 or an ARINC 429 data bus. It also provides via the TC978 an altitude

data output of the pressure altitude used in the ADS-B message.

1.4.3 Control Panel

The FDL-978 Series can interface with a transponder, a GSL-71 Control Panel via an RS-232 bus

or a TC978 controller via an RS-485 bus. Additionally, certain Multi-Function Displays such as

the MX 20, GMX 200, and the Aspen EFD 1000 PFD series can act as a controller for the FDL-

978.

1.4.4 Annunciator Output

The FDL-978 Series can display required annunciation messages on an approved MFD connected

through an RS-422 or RS-232 bus, or the TC978 controller using the RS-485 bus and also has a

single discrete output to drive an amber remote Annunciator Light when the TC978 controller or

suitable display is not installed.

1.4.5 External GPS/WAAS Sensor Interface

The FDL-978 Series can interface with an approved GPS/WAAS Sensor. See Section 2.8 for a

list of approved GPS/WAAS Sensors.

1.4.6 Maintenance Interface

The preferred method for accessing the Maintenance Port interface on the FDL-978 is by

connecting the Wi-Fi Maintenance Port Interface (MPI) module to one of two optional RS-232

buses. This is a temporary connection that must be removed before maintenance release of the

airplane.

Capstone-II-0103


A special USB to Serial Adapter Module (P/N 86971-00-2) is required to connect the FDL-978

Series Maintenance port to a Personal Computer (PC) for the purpose of configuring the system

with a terminal program such as Terra Term. Refer to the FDL-978 Series Installation Manual

(P/N 87343 current revision), Maintenance Interface Diagrams, for interconnect wiring.

After the release of software version E, an additional RS232 serial port maintenance interface is

provided. See the FDL-978 Series Installation Manual (P/N 87343 current revision) for wiring

and interface instructions.

1.5 Antenna Requirements (Ref CS-0103-ANT drawing)

Antenna performance is critical to the GPS/WAAS operation.

1.5.1 UAT Antennas

The FDL-978 Series requires a TSO-C66, C74, C112, or C154 UHF antenna(s). Ensure that the

antenna has 50Ω impedance with a VSWR < 1.7:1 at 978 MHz. The Comant CI-101 and RA

Miller AV-22 ball antennas and the Comant CI-105 blade antenna meet these requirements. In

Class A1H ADS-B equipment (TSO-C154c) installations, antenna diversity (meaning a top and

bottom antenna) is required. In Class A1S (single antenna) installations only one antenna (top or

bottom) is used. For airworthiness approval of ADS-B out systems (AC 20-165) single bottom

mounted antenna (TSO-C154c Class A1S) installations are allowed.

1.5.2 GPS Antennas for FreeFlight GPS/WAAS

The FDL-978 Series requires any TSO-C144 (DO-228) or TSO-C190 (DO-301) compliant

antenna. Installation of a TSO-C190 antenna is only recommended for anticipated future upgrades

to TSO-C145c Class Beta 2, 3 or 4 navigation sensors and avoids the need for a GPS antenna

change at that time.

The performance of the FDL-978 Series internal GPS is affected by the gain, noise figure,

impedance, and frequency selectivity characteristics of the antenna. FDL-978 should be used only

with the recommended antenna and cable. Use of other antennas or cable may not meet all the

performance characteristics required by TSO-C145c.

1.6 Test Equipment

1.6.1 Required Test Equipment

1. Digital Multimeter

2. FreeFlight Systems manufactured ADS-B OUT Ramp Tester

1.6.2 Required Test Equipment for Certain Installations

1. Milliohm Meter

2. Pitot-Static Test Set

3. ATCRBS Transponder Ramp Test Set

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1.7 Weight and Balance

Note: It is the aircraft operator’s responsibility to update the aircraft’s weight and balance records based

upon the actual arm (fuselage station) of the installed equipment.

The following table shows the weights for the FreeFlight Components.

Added Equipment

Equipment Weight

TC-978 Controller 4 + 0.11 lbs

Altitude Digitizer 1 + 0.32 lbs

GPS Antenna + 0.50 lbs

1201 GPS/WAAS Sensor 2 + 1.20 lbs

FTM-190C Transponder Monitor 3 + 0.26 lbs

FDL-978 Series with GPS + 0.98 lbs

FDL-978 Series without GPS + 0.86 lbs

Quick Change Rack + 4.80 lbs

Table 2

Note: 1. Altitude Digitizer is optional. If not installed disregard weight data.

2. A GPS/WAAS sensor such as the 1201 GPS/WAAS Sensor is required when non-existent on

the aircraft. If the aircraft has an existing 1201 GPS installed disregard weight and balance data.

3. FTM-190C Monitor is optional. If not installed disregard weight data.

4. TC978 Controller is optional. If not installed disregard weight data.

1.8 Electrical Load

Note: It is the aircraft installer’s responsibility to update the aircraft’s electrical load analysis based upon

the actual electrical bus that the equipment is connected to and to take into consideration any removed

electrical loads.

Electrical Loads

14V DC Bus Flight Phase

C/B Equipment Cont

Load

Loading Eng.

Start

Taxi T/O

Climb

Cruise Landing

ADS-B

FDL-978 Series 0.20 A 0.20 A 0.20 A 0.20 A 0.20 A 0.20 A 0.20 A

FTM-190C 0.06 A 0.06 A 0.06 A 0.06 A 0.06 A 0.06 A 0.06 A

WI-FI 0.06 A 0.06 A 0.06 A 0.06 A 0.06 A 0.06 A 0.06 A

GPS 1201

GPS/WAAS2 0.50 A 0.50 A 0.50 A 0.50 A 0.50 A 0.50 A 0.50 A

ALT

ENCODER

Altitude

Digitizer1

0.25 A 0.25 A 0.25 A 0.25 A 0.25 A 0.25 A 0.25 A

Table 3

28V DC Bus Flight Phase

C/B Equipment Cont

Load

Loading Eng.

Start

Taxi T/O

Climb

Cruise Landing

ADS-B

FDL-978 Series 0.10 A 0.10 A 0.10 A 0.10 A 0.10 A 0.10 A 0.10 A

FTM-190C 0.04 A 0.04 A 0.04 A 0.04 A 0.04 A 0.04 A 0.04 A

WI-FI 0.04 A 0.04 A 0.04 A 0.04 A 0.04 A 0.04 A 0.04 A

GPS 1201

GPS/WAAS2

0.25 A 0.25 A 0.25 A 0.25 A 0.25 A 0.25 A 0.25 A

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ALT

ENCODER

Altitude

Digitizer1

0.27 A 0.27 A 0.27 A 0.27 A 0.27 A 0.27 A 0.27 A

Table 4

Note:

1. A GPS/WAAS sensor such as the 1201 GPS/WAAS Sensor is required when non-existent on

the aircraft when the FDL-978 Series without an internal GPS receiver, (P/N 87098-10-XXXX) is

installed in the aircraft.

2. FDL-978 Series also comes with internal transponder monitor. If this unit is used FTM-190C is

not required.

1.9 References

1. Manufacturer’s Data

Data Number Title

87343 Equipment Installation Manual for the FreeFlight Systems FDL-978 Series

Transmitter

84739 Addendum to Equipment Installation Manual for the FreeFlight Systems

1201 GPS/WAAS SENSOR

86961 FreeFlight Systems FDL-978 Series ADS-B Transmitter Pilot Guide / User

Manual

86963 FreeFlight Systems FDL-978 Series Transmitter (P/N 85595-00) Quick

Reference Guide

87114 Equipment Installation Manual for FreeFlight Systems FTM-190C

Transponder Monitor (P/N 86930-00)

87330 FreeFlight Systems Installation Manual for the WI-FI Hotspot Transmitter

882188 Trans-Cal Industries Model SSD120-(XX)N(X) All Solid State Altitude

Encoder/Digitizer Owner/Installation Manual

103079 Adapter Plate (Ameri-King) Installation Drawing

114-10038 Circular Plastic Connectors (CPC)

SerialPortConf882237rA

.pdf

Trans-Cal Industries, Inc. Document 882237 Rev. A.: Serial Port One-Foot

Resolution Configuration Procedure Altitude Digitizers Models SSD120-

(XX)A-RS232.

Table 5

2. FAA Advisory Circulars

AC Number Title AC 20-165A Airworthiness Approval of Automatic Dependent Surveillance – Broadcast

(ADS-B) Out Systems

AC 20-172A Airworthiness Approval for ADS–B In Systems and Applications

AC 43.13-1B Acceptable Methods, Techniques, and Practices – Aircraft Inspection and

Repair

AC 43.13-2B Acceptable Methods, Techniques, and Practices – Aircraft Alterations

AC 43-6C Altitude Reporting Equipment and Transponder System Maintenance and

Inspection Practices

Table 6

1.10 Project Data List

Drawing No. Title

CS-0103-WD Wiring Diagram Rangr ADS-B

CS-0103-RT FFS ADS-B Wire Routing Drawing

CS-0103-ANT FFS ADS-B Antenna Installation Drawing

Capstone-II-0103


CS-0103-SEN FFS ADS-B Equipment Installation Drawing

Table 7

1.11 Definitions and Acronyms

ADC Air Data Computer

ADS-B Automatic Dependent Surveillance – Broadcast

AHRS Attitude Heading Reference System

ALT Altitude

APM Aircraft Personality Module

C/B Circuit Breaker

CDTI Cockpit Display of Traffic Information

EN Engineering Notice

EFD Electronic Flight Display

FIS-B Flight Information Services – Broadcast

GPS Global Positioning System

MFD Multi-Function Display

PFD Primary Flight Display

QCR Quick Change Rack

RCEP Rule Compliant Equipage Program

SBAS Satellite Based Augmentation Systems

STC Supplementary Type Certificate

TIS-B Traffic Information Service – Broadcast

TSO Technical Standard Order

UAT Universal Access Transceiver

VSWR Voltage Standing Wave Ratio

WAAS Wide Area Augmentation System

Capstone-II-0103


2 Installation

This section describes the installation of the FDL-978 Series including mounting, wiring, and

connections.

2.1 Pre-Installation Information

When using this manual always also follow acceptable avionics installation practices per FAA Advisory

Circulars AC 43.13-1B (Chapters 1, 2, 3, 11, 13) Acceptable Methods Techniques and Practices-Aircraft

Alteration, AC 43.13-2B (Chapters 1, 2, 3, 11) Acceptable Methods Techniques and Practices-Aircraft

Alteration, SAE AS50881 Wiring Aerospace Vehicle (Chapters 3-1 through 3-24, 6-1 through 6-8),

SAE ARP1870 (Chapters 4,5) Aerospace Systems Electrical Bonding and Grounding for

Electromagnetic Compatibility and Safety. Always use latest FAA accepted revisions of these

documents. “Best Practices” design details of installation data specified within are derived from aircraft

and equipment manufacturer’s data and maintenance/vendor manuals and include design details from

these data. Design details specified within (bonding, grounding, wire routing, separation, EMI/Lightning

protection, materials, composites, structures, etc) this document shall take precedence over the data

listed only in areas defined within. Wiring types to be used for installation are specified below and on

design data noted.

Follow the installation procedure in this section as it is presented for a successful installation. Read

the entire section before beginning the procedure. Prior to installation, consider the structural integrity

of the FDL-978 Series installation as defined in AC 43.13-2B, Chapter 1. Perform the post

installation checkout before closing the work area in case problems occur.

Complete an electrical load source assessment in accordance with AC 43.13-1B, Chapter 11 or later

approved revision on the aircraft prior to starting modification to ensure aircraft has adequate power

available for the FDL-978 Series system loads. Refer to Section 1.8 for the power consumption of

each system component. Document the results of the electrical load assessment on FAA Form 337.

2.2 Installation Overview

A successful installation should start with careful planning, including determination of mounting

location for the FDL-978, Series cable routing, if CDTI is installed and other required modifications

and system configuration requirement. Table 1 should be evaluated for acceptable installation

configurations based on aircraft installed equipment. Once the mounting location has been

determined, prepare the mounting tray for installation. It may be easier to complete the wiring and

attach the connectors to the tray upon installation.

2.3 Material Required But Not Supplied

Wire (MIL-W-22759/16) or equivalent.

Shielded wire (MIL-DTL-27500)

MIL Standard Circuit Breakers

Ring Terminals (for grounding)

NOTE: Specific materials defined on system wiring diagram (CS-0103-WD)

2.4 Special Tools Required

Some of the connectors use crimp contacts. Table 2-1: Special Tools below identify crimp tools

required to ensure consistent, reliable crimp contact connections for the rear D-sub connectors. The

table defines one source for the crimp tool. Alternate equivalent tools may be used.

Capstone-II-0103


Table 2-1: Special Tools

Description ITT/Cannon P/N Military No. Industry No. Insertion/Extraction tool CIET-20HD

980-200-426 M81969/39-01

Crimp tool 995-0001-584 M22520/2-01

Positioner 995-0001-604 M22520/2-08

Multi volt-ohmmeter Simpson 260 or equiv

2.5 Equipment Mounting

2.5.1 Cabling and Wiring

Wiring should be installed in accordance with design data and other referenced standards including AC

43.13-1B Chapter 11 and SAE AS50881 as noted. When wire separation cannot be achieved, the

following issues should be addressed:

• The cable wiring should not be located near flight control cables and controls, high

electrical capacity lines or fuel lines.

• The cable wiring should be located in a protected area of the aircraft.

• Do not route cable near high-energy sources.

• Maintain a minimum separation of 2 inches from Fuel Quantity Wiring.

• Install wiring following existing bundles where practical. Refer to FreeFlight drawing number CS-0103-WD wiring diagram in Appendix A for the appropriate

wiring. Route the wiring bundles in accordance with FreeFlight wire routing drawing number CS-0103-

RT. Use wire gauges as defined on CS-0103-WD wiring diagram for all connections. Avoid sharp bends.

2.5.2 FDL-978 Series Mounting

The FDL-978 Series does not require forced-air cooling; however, when mounting the FDL-978

Series, avoid locating the FDL-978 Series near sources that produce high levels of heat. The tray can

be installed in a variety of locations, such as the electronics bay, under a seat or behind the rear

baggage area. Refer to FreeFlight Equipment Installation drawing number CS-0103-SEN for

suggested locations. Leave sufficient clearance between the FDL-978 Series and any obstruction.

Install tray in accordance with AC 43.13-2B Chapter 2 Communication, Navigation, and Emergency

Locator Transmitter System Installations. Tray should be mounted to a surface known to have

sufficient structural integrity to withstand additional inertia forces imposed by a 6.4-pound unit. If it

is necessary to build a shelf or bracket to mount the FDL-978 Series tray or it is not certain that the

chosen location is of sufficient structural integrity, refer to FreeFlight Equipment Inst’l drawing

number CS-0103-SEN.

Ensure that the FDL-978 Series chassis has a ground path to the airframe by having at least one

mounting screw in contact with the airframe.

For the best resistance to moisture, install the tray in the upright vertical orientation.

Prepare the optional Personality Module (PM) wires by stripping the leads and crimping the contacts.

Do not extend the length of the PM wires.

Secure the PM by adhering one side of the double sided tape to the PM and the other side to one side

of the connector backshell as the connector and backshell are assembled together.

Capstone-II-0103


Insert the PM leads into the correct locations on connector P1XVR1.

2.5.3 Antenna Installation and Connections

The FDL-978 Series requires 2 antennas for non-diversity, and three antennas for diversity

installations; one GPS antenna (if a FreeFlight GPS installation is used as the position source) and

one to two UAT antennas. Single-UAT-antenna installation must be mounted on the bottom of the

airplane. Single-antenna installations are permitted according to AC 20-165A. FreeFlight Systems

strongly recommends two UAT antennas be used for all installations, where possible.

For mounting both the GPS and UAT antennas, refer to FreeFlight Antenna Installation drawing

number CS-0103-ANT.

2.5.4 GPS Antenna for a FreeFlight GPS installation

The GPS antenna is a key element in the overall system performance and integrity for a GPS/WAAS

system. The mounting location, geometry, and surroundings of the antenna can affect the system

performance and/or availability. The following guidance provides information to aid the installer in

ensuring that the most optimum location is selected for the installation of the GPS antenna. The

installation guidelines presented here meet the intent of AC 20-138A section 16. The greater the

variance from these guidelines, the greater the chance of decreased availability. Because meeting all of

these installations guidelines may not be possible on all aircraft, these guidelines are listed in order of

importance to achieve optimum performance. Items 3a, 3b, and 3c below are of equal importance and

their significance may depend on the aircraft installation. The installer should use their best judgment

to balance the installation guidelines.

1. Mount the antenna as close to level as possible with respect to the normal cruise flight attitude of

the aircraft. If the normal flight attitude is not known, substitute the waterline, which is

typically referenced as level while performing a weight and balance check.

2. The GPS antenna should be mounted in a location to minimize the effects of airframe

shadowing during typical maneuvers. Typically mounting farther away from the tail section

reduces signal blockage seen by the GPS antenna.

3a. The GPS antenna should be mounted no closer than two feet from any VHF COM antenna or

any other antenna, w h i c h may emit harmonic interference at the L1 frequency of 1575.42

MHz. An aircraft EMC check ( r e f e r e n ce S e c t i on 9 o f t h es e i n s t a l l a t i o n s

i n s t r u c t i o n s ) can verify the degradation of GPS in the presence of interference signals. If

an EMC check reveals unacceptable interference, insert a GPS notch filter in line with the

offending VHF COM or the (re-radiating) ELT transmitter.

Note: When mounting a combination antenna, the recommended distance of two feet or more is not

applicable to the distance between the antenna elements in a combination antenna (ex. GPS and

COM, GPS and XM) provided the combination antenna is TSO authorized and has been tested to

meet FreeFlight’s minimum performance standards.

3b. The GPS antenna should be mounted no closer than two feet from any antennas emitting more

than 25 watts of power. An aircraft EMC check can verify the degradation of GPS in the presence

of interference signals.

3c. To minimize the effects of shadowing at 5° elevation angles, the GPS antenna should be mounted

no closer than 6 inches (edge to edge) from other antennas, including passive antennas such as

another GPS antenna or XM antenna.

4. To maintain a constant gain pattern and limit degradation by the windscreen, avoid mounting

the antenna closer than 3 inches from the windscreen.

5. For multiple GPS installations, the antennas should not be mounted in a straight line from the front

Capstone-II-0103


to the rear of the fuselage. Also varying the mounting location will help minimize any aircraft

shading by the wings or tail section (in a particular azimuth, when one antenna is blocked the

other antenna may have a clear view).

Refer to FreeFlight Antenna Installation drawing no. CS-0103-ANT (Appendix D) for

recommended placement of antennas.

2.5.4.1 NOTE

If using an approved GPS antenna that was already on the aircraft, or if mounting the antenna closer than recommended distance from other antennas, conduct the GPS/VHF Comm Interference Check in S e c t i o n 9 o f t h e s e i n s t a l l a t i o n i n s t r u c t i o n s . If the FDL-978 installation passes the test, then the GPS antenna performance is acceptable for non-navigation use.

RF connectors and RG-142 coax cable are included in the installation kit. Assembly instructions for the

connectors are included. Proper assembly of the connectors is critical to GPS receiver performance and

reliability. Other equivalent airworthy parts may be used.

SATCOM:

The FDL-978 Series is approved for installation on aircraft that have SATCOM equipment installed

with some GPS/WAAS antennas.

Cable Loss:

For antennas listed in applicable Tables with FDL-978 Series units containing GPS/WAAS V2.4 or

earlier software: the signal loss from the GPS antenna cable shall be at least 3 dB and shall not be

greater than 7 dB to maintain proper rejection to interference signals. Allow 3.5 dB loss for each

branch of a 2-way splitter if a GPS splitter is used.

For antennas listed in Table 1-1 with FDL-978 Series units containing V3.0 or later GPS/WAAS

software: the signal loss from the GPS antenna cable shall be at least 1.5 dB and shall not be greater

than 6.5 dB to maintain proper rejection to interference signals. Allow 3.5 dB loss for each branch of

a 2-way splitter if a GPS splitter is used.

When calculating cable losses; include the loss due to each connector or RF adapter (typically 0.2

dB) used in the GPS antenna cable assembly. If using RG-142B or RG-400 cable up to 35 feet long

can be used. (1.5 dB equates to a length of approximately 6.5 feet of RG-142B or RG-400 cable with one

connector on each end.) For longer cable lengths, use low-loss double or triple shielded 50-Ohm coax.

For very short runs where the loss is less than 3 dB, additional cable can be used to increase the loss.

This additional cable may be coiled, taking into account the minimum bend radius of the cable.

Routing and Checkout:

Once the antenna mounting position has been prepared, route the coax cable from the antenna to the

FDL-978.

During the post-installation checkout, evaluate the GPS susceptibility to harmonics from all VHF

transmitters on the aircraft. If interference with the GPS is found, the problem must be resolved before

the installation is completed. Interference may be minimized through using of double shielded VHF

antenna coax, VHF radio grounding and shielding, increasing the distance between the GPS and comm

antennas, or by installing a 1575.42 MHz notch filter in series with the antenna coax of the VHF

comm transceiver.

Capstone-II-0103


If a VHF comm transmitter causes interference with GPS reception, the problem may be due to the

ELT. This can be verified by disconnecting the ELT antenna coax at the ELT unit and repeating the

test. If the ELT is found to cause the problem, then contact the ELT manufacturer or replace the ELT.

FIG 1

2.5.5 UAT Antennas

The UAT antenna is a standard 50Ω vertically polarized L-band antenna that operates at 978 MHz.

Any antenna meeting the requirements of TSO-C66, C74, C112 or C154 and presenting a VSWR of

less than 1.7:1 at 978 MHz is acceptable. Garmin AT Model A-40 and A-41 antennas meet these

requirements, and are suitable for use in both fixed-wing aircraft and rotorcraft. UAT antennas must

be mounted more than 0.5 meters from any FADEC (Full Authority Digital Engine Control). Follow

the manufacturer’s instructions for installing the antennas.

The FDL-978 receives UAT signals from antennas on the top and bottom of the fuselage or a single

antenna on the bottom of the fuselage. Because UAT signals propagate by line-of-sight, simultaneous

shadowing of the antennas should be avoided. Shadowing may be from vertical stabilizers or wings,

other antennas, engines, propellers, or the fuselage itself. Selection of appropriate antenna locations is

critical to the proper performance of the FDL-978.

2.5.5.1 CAUTION

Operating the FDL-978 without RF terminations on the Top or Bottom UAT Antenna ports can result in equipment damage. Always operate the FDL-978 with the Top and Bottom UAT Antenna ports terminated with a VSWR ratio of 1.7:1 or less.

Capstone-II-0103


2.5.6 UAT Antenna Ground Plane

When a conventional aircraft monopole antenna is used it relies on a ground plane for correct operation.

For ideal performance the ground plane should be very large compared to the wave length of the

transmission, which is ~12in. In a metal skinned aircraft this is usually easy to accomplish, but is more

difficult in a composite or fabric skinned aircraft. In these cases a metallic ground plane should be

fabricated and fitted under the antenna.

As the ground plane is made smaller, the actual dimensions of the ground plane become more critical, and

small multiples of the wavelength should be avoided, as should circles. Rectangles of squares are much

less likely to create a critical dimension that resonates with the transmissions. The smallest practical

ground plane is a square around 5.25 in. per side; as the size increases the performance may actually get

worse, but will be better by the time the ground plane is 30.5 in. on each side. Anything much larger than

that size is unlikely to show significant further improvement.

The thickness of the material used to construct the ground plane is not critical, providing it is sufficiently

conductive. A variety of mesh and grid solutions are available.

2.5.7 UAT Antenna Cable

The FDL-978 is designed to meet Class A1H/A1S requirements with an allowance of 2 – 6 dB for loss in

the connectors and cable used to connect it to the antenna. Excessive loss degrades transmitter output

power so it is recommended that the installation cable loss be limited to the loss minimum of 2 – 2.5 dB.

Allowing 0.25dB loss for the connector at each end of the antenna cable assembly leaves an allowance of

1.5 – 5.0 dB loss for the cable itself.

An acceptable cable then has:

A minimum of 1.5 dB loss for the run length but no greater than 5.0 dB loss

A characteristic impedance of 50 ohms

Double braid screens or has a foil and braid screen

Once the cable run length is determined, a cable type with the proper attenuation (loss) per foot that meets

the above requirements can be chosen. Longer runs require lower loss cable. Consider moving the FDL-

978 closer to the antenna to minimize the losses in the antenna cable subject to the limits identified above.

The following table is a guide to the minimum and maximum usable lengths of some common cable

types. Actual cable loss varies between manufacturers and the table is based on typical data. Use the table

as a guide only and refer to the manufacturer’s data sheet for the specific cable chosen to calculate the

minimum and maximum lengths. Proper coax cable connector assembly is a critical step and can cause

excess loss if improperly done. Once cable type is selected below connectors shall be assembled in strict

compliance to FIG 1 above, component manufacturer’s instructions and AS50881 paragraph 3.8.4.

NOTE: After assembly proper function shall be verified as part of overall system functional test. Any

poor system performance or system power loss as indicated during test shall include investigation of

connector assembly.

Cable Attenuation

(dB/100 ft @ 1 GHz

Minimum Length

(ft)

Maximum Length

(ft)

RG-174 27.1 5.5 18.5

RG-316 25.8 5.8 19.4

RG-400 14.5 10.3 34.5

RG-142 12.8 11.7 39.1

RG-393 7.5 20 66.7

Table 9

When routing the cable, ensure the following:

Capstone-II-0103


Route the cable away from sources of heat.

Route the cable away from potential interference sources such as ignition wiring, 400Hz

Generators, fluorescent lighting, and electric motors.

Allow a minimum separation of 12 inches (300mm) from an ADF antenna cable.

Keep the cable run as short as possible.

Avoid routing the cable around tight bends.

Avoid kinking the cable even temporarily during installation.

Secure the cable so that it cannot interfere with other systems.

2.6 Optional Installation Kits

Part Number Description

85935-00 FDL-978-XVR Installation Kit (Also used for –RX)

87002-10 FDL-978-XVR Personality Module Installation Kit (Also used for –RX)

86964 TC978 Controller Installation Kit (*As Needed)

87003-00 UAT Blade Antenna Installation Kit (*As Needed)

87004-00 UAT Ball & Stick Antenna Installation Kit (*As Needed)

87360-10 TSO-C144 GPS Antenna Installation Kit (*As Needed)

87360-00 TSO-C190 GPS Antenna Installation Kit (*As Needed)

87113-00 FTM-190C Transponder Monitor Installation Kit (*If Installed)

87231-00 WI-FI Installation Kit (*If Installed)

Table 10

The contents of each Installation Kit are listed in the Bill Of Materials on the Wiring Diagram

RANGR ADS-B drawing number CS-0103-WD.

Note: Some of the materials listed may not be required for all installations and can be considered

excess.

2.7 Equipment Required Per Aircraft

Qty Part Number Description Manufacturer

A/R 87098-00-FX00 FDL-978-XVR FreeFlight Systems

A/R 87098-10-FX10 FDL-978-XVR w/o GPS FreeFlight Systems

A/R 87098-00-FR00 FDL-978-RX FreeFlight Systems

A/R 87098-10-FR10 FDL-978-RX w/o GPS FreeFlight Systems

A/R 87098-00-FT0L FDL-978-TXL FreeFlight Systems

A/R 87098-00-FX0L FDL-978-XVRL FreeFlight Systems

A/R 81194 GPS Antenna TSO-C144 FreeFlight Systems

A/R 86735 GPS Antenna TSO-C190, C144 FreeFlight Systems

A/R 87005 L-Band Antenna, Blade Type FreeFlight Systems

A/R 85937 L-Band Antenna, Ball & Stick Type FreeFlight Systems

Permitted Software Versions

Device (if installed) Permitted Software Version

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87098-XX-XXXX

System Version 001E (software version 1.9.1.187) or

System Version 001F (software version 1.10.1.99)

or later FAA-approved version

TC-978 UAT Controller Software Version 1.13 or later FAA-approved version

Aspen EFD1000 PFD

Aspen EFD1000 MFD

Aspen EFD500 MFD

MAP 2.7.2 or later FAA-approved version

IOP 2.0.5 or later FAA-approved version

MX20 MFD Software Version 5.7

GMX 200 MFD Software Version 2.12 or later FAA approved version

Garmin GSL 71 UAT Control Panel No Software Version is Identified

Chelton FlightLogic EFIS Software Version 6.0B

Wi-Fi Module All software versions

Model 1201 GPS as a Position

Source Software Version 0306 or later FAA-approved version

Garmin 400W/500W Series as a

Position Source and/or ADS-B IN

traffic source.

Main Software Version 5.03 or later

GPS Software Version 5.00 or later

Table 2-2: Required and Optional Equipment - Software Versions

2.8 Approved Optional Equipment

In accordance with 14 CFR 91.217 (b), the transponder and the FDL-978UAT (ADS-B

equipment) must obtain pressure altitude information from the same source. If the existing

pressure altitude reporting equipment does not output RS-232 data that is compatible with the

FDL-978 UAT then pressure altitude reporting equipment that is compatible with both the

transponder and FDL-978 UAT must be installed.


1 ea. 00808-00-04 TC978 Controller FreeFlight Systems

1 ea. 84100-03-0304 1201 GPS/WAAS Sensor as

a Position Source

FreeFlight Systems

1 ea. 86930-00-101A FTM-190C XPDR Monitor FreeFlight Systems

1 ea. 86943-00 Serial to WiFi Transceiver

(Wi-Fi Module)

FreeFlight Systems

1 ea. SSD120-(XX)-N(X) Altitude Digitizer Trans-Cal Industries

1 ea. 011-01057-(__)

GPS 400W as a Position

Source and/or ADS-B IN

traffic source.

Garmin

1 ea. 011-01058-(__)

GNC 420W as a Position


traffic source.

Garmin

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1 ea. 011-01059-(__)

GNC 420AW as a Position


traffic source.

Garmin

1 ea. 011-01060-(__)

GNS 430W as a Position


traffic source.

Garmin

1 ea. 011-01061-(__)

GNS 430AW as a Position


traffic source.

Garmin

1 ea.

011-01062-(__)

GPS 500W as a Position


traffic source.

Garmin

1 ea. 011-01063-(__)

GPS 500W TAWS as a

Position Source and/or

ADS-B IN traffic source.

Garmin

1 ea. 011-01064-(__)

GNS 530W as a Position


traffic source.

Garmin

1 ea.

011-01065-(__)

GNS 530W TAWS as a



Garmin

1 ea. 011-01066-(__)

GNS 530AW as a Position


traffic source.

Garmin

1 ea. 011-01067-(__)

GNS 530AW TAWS as a



Garmin

Table 2-3: Approved Optional Equipment

2.8.1 Optional Altitude Digitizer Adapter Plates

If the optional Altitude Digitizer part number SSD120-(XX)-N(X) is used then one of the

adapter plates listed below may be required.


1 ea. 103035 Adapter Plate Trans-Cal Industries






Table 2-4: Altitude Digitizer Adapter Plates

2.9 Reserved

2.10 Personality Module (PM)

The FDL-978 Series stores installation-specific configuration information in an aircraft personality

module located inside the P1 connector backshell. This eliminates the need to set up the

configuration again if a new FDL-978 Series is installed. Since PM contains no lightning protection,

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the wire length from the PM to the FDL-978 Series must be limited to 4 inches maximum. Refer to

the FreeFlight Wiring Diagram drawing number CS-0103-WD for connection information.

2.11 CDTI (Multifunction Display)

If a CDTI (Multifunction Display) is installed in the aircraft ensure that the display is

configured/enabled for Traffic Alert as described in the GDL 90 Data Interface Specification Rev. A or

“traffic, FIS” modes as applicable in accordance with manufacturer’s instructions (e.g. Aspen EFD1000

and EFD500 reference Appendix J:ATX100 and ATX100G Transceiver Installation Information in the

EFD1000 and EFD500 Software Version 2.X Installation Manual Document 900-00003-001 Revision

AZ or later revision; MX20 reference manuals 560-1025-09, section 2.9.3., Rev F or later; GMX200

reference 190-00607-04, section 5, Rev F or later). Other installed displays shall also be configured/

enabled for Traffic Alert as described in the GDL 90 Data Interface Specification Rev. A or “traffic,

FIS” modes in accordance with equipment manufacturer’s manuals.

2.12 Status LEDs

The FDL-978 Series uses 4 LEDs mounted on the front of its enclosure to communicate system

status and conditions of various internal functions. The descriptions of the LEDs, with power

applied to the unit, are as follows:

Name Description

STATUS UAT System Status (RED)

ON UAT failure. Troubleshoot system.

OFF UAT is operating normally.

Flash Fast GPS fault condition or no position available

GPS GPS Status (GREEN)

Flash Slow GPS is acquiring satellites and determining position.

Flash Fast GPS reporting a fault condition.

ON GPS has acquired satellites and is operating normally.

OFF GPS is not communicating.

TX UAT Transmit (GREEN)

Blink ON Blinks ON when ADS-B data is transmitted (once per second)

OFF No UAT transmissions

RX UAT Receive (GREEN)

Blink ON Blinks ON when ADS-B data is received

OFF No UAT receptions

Table 2-5: LED Descriptions

2.13 Discrete Inputs

2.13.1 Air/Ground Input

The Air/Ground discrete input can be connected to an open/ground squat switch or other Air/Ground

discrete indication. The Air/Ground discrete is configurable to be either Not Connected, High when

Airborne, or Low (ground) when Airborne. The FDL-978 Series automatically determines air/ground

state based on several factors: Emitter Category type, Airspeed (if available), groundspeed, and

Air/Ground discrete input.

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2.13.2 Traffic Test Input

The Traffic Test Input indicates the traffic test status of a 429 traffic display. The FDL-978 Series will

send traffic test data to ARINC OUT 1 when the traffic test input is active.

2.14 Discrete Outputs

Discrete outputs can be used to drive annunciator lamps or provide status information to other

equipment. Unless otherwise indicated, they are active low (i.e. grounded when active, and open

otherwise) and open collector output capable of sinking up to 400 ma.

2.14.1 ADS-B Status Output

The UAT Status indicates the status of the FDL-978 Series or status of its GPS receiver. The UAT

Status output is an active low, open collector output capable of sinking a maximum of 100 mA. The

UAT status output indicates a UAT system failure when grounded. Note that the UAT system failure

includes the loss of valid GPS data from the GPS system.

As UAT Fail Indicator The UAT status output indicates a UAT transmit or receive system

failure when continuously grounded. UAT status output also indicates

the loss of valid GPS data from an internal or external GPS. If the

internal or external GPS is not functioning, reporting a failure, or

reporting invalid GPS position data, this discrete will toggle between

ground and open at a rate of approximately 4 times per second.

This discrete is typically used if installed display does not provide

UAT failure annunciation, and the control panel does not provide a

FDL-978 Series status monitor. In this case, install an annunciator

lamp in the aircraft.

As GPS Status Indicator The UAT Status Out will flash (i.e. alternate between being open

and grounded) at a 1 Hz rate when the FDL-978 Series GPS is

searching but has not acquired a position.

2.14.2 TX Suppression Output

The TX Suppression Output is for suppressing other L-band equipment during UAT transmissions. TX

Suppress outputs a high (Vin – 1.5 V) only during UAT ADS-B message transmissions and is low

otherwise. The TX Suppress output is typically connected to the transponder suppression bus.

2.15 Time Mark Input / Output

For the FDL-978-RX/XVR, the Time Mark Input / Output is an RS-422 differential pair for the one

pulse-per-second (PPS) input from an external GPS or output when the Transceiver/Receiver has an

internal GPS. The Time Mark input/output from a GPS provides the timing synchronization for sending

ADS-B messages.

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3 Accomplishment Instructions – General Notes, Access & Figures

3.1 Pre-installation Considerations

1. Verify previously installed equipment: Determine functionality, Note issues before beginning

install. All repairs, or modifications, to previously installed equipment are the responsibility of

the owner. This list is only a guide. Table 1 Approved Configurations indicates the compatible

equipment.

a. Transponder

i. Type - (Mode A/C analog; Mode A/C digital output; Mode S with digital output;

Mode S without digital output; Mode ES with or without digital output)

ii. Quantity –

1. Single

2. Multiple – same type; different types

b. MFD

i. Serial Input – RS422; RS232

1. MX-20 data format

2. Traffic Alert format (refer to the GDL 90 Data Interface Specification

Rev. A)

ii. ARINC input –

1. Intruder Format

2. ADS-B Format

c. Altitude Source – (Must be the same source for the Transponder and the ADS-B)

i. Encoder

1. Trans-Cal

a. Single encoder

b. Multiple encoders

2. Other

a. Single encoder

b. Multiple encoders

ii. ADC

1. Serial data

2. ARINC data

d. Controller for single-point of entry

i. MFD

1. MX-20

2. GMX-200

ii. Transponder

1. SL-70/R

2. GTX (GTX-32, GTX-33, GTX-327, GTX-328, GTX-330)

3. KT73, KT76/78, KXP, TDR 950 TDR 90, TDR 94D

iii. Control Head

1. TC-978

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2. GSL-71

e. Antennas

i. GPS (for FreeFlight GPS installation)

1. WAAS

2. Non-WAAS

3. None

ii. UAT

1. Single

2. Dual

3. None

iii. Cables

1. Integrity

2. Impedance

3. Connectors

2. Determine approximate locations for new equipment.

a. The Failure Annunciation device must be within the pilot’s primary field of view. One of

the following must be the Failure Annunciation Device.

i. TC-978

ii. MFD – capable of receiving and displaying status from the FDL-978

iii. Annunciator Light

b. FDL-978 Location:

i. Dry location not exposed to weather or excess heat.

c. UAT Antenna Location:

i. See STC drawing package for approved locations.

d. GPS WAAS Antenna Location (for FreeFlight GPS installation):

i. See STC drawing package for approved locations.

ii. Must have clear, unobstructed view of the sky during normal aircraft maneuvers.

3. Determine cable and wire routing plan.

a. Dry location not exposed to excess heat.

4. If a GSL-71 is used as the control head for the FDL-978, the Serial Baud rate must be set to 9600.

This is accomplished by setting the serial altitude input to Shadin (1ft.) format. If a Trans-Cal,

Inc. SSD120-(XX)A-RS232 altitude digitizer is installed in the aircraft, the digitizer can be

reconfigured to output data in the 1ft. format at 9600 Baud by following the procedure outlined in

Trans-Cal, Inc. document SerialPortConf882237rA.pdf.

Note: It is not necessary to follow the exact order of the accomplishment instructions as they are

listed. It is up to the discretion of the person(s) performing the installation as to what order is

the most logical to perform the necessary tasks.

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Note: The drawings referred to in these accomplishment instructions are typical for the aircraft listed

in FreeFlight Systems documents CS-0103-WD, CS-0103-RT, CS-0103-ANT and CS-0103-

SEN. It is the responsibility of the installer to determine compatibility of this design change

with the current configuration and previously approved modifications.

1. Electrically ground the aircraft prior to any maintenance being performed.

2. Remove power from the aircraft per the aircraft maintenance manual.

3. Remove the battery connector from the main battery of the aircraft per the aircraft

maintenance manual.

4. Gain access for the installation of the UAT Equipment Shelf Assembly.

5. Gain access for the wire wiring routing and installation.

6. Gain access for the installation of the GPS antenna and top UAT antenna.

7. Gain access for the installation of the bottom UAT antenna.

8. Gain access for the installation of the circuit breakers.

9. Gain access for installation of the TC978 Controller.

10. Configure any installed CDTI

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4 Accomplishment Instructions – Mechanical

4.1 General Guidelines:

In all cases the design drawings specified for a given aircraft take precedence over these general

guidelines. These guidelines should be used in conjunction with specified design data and other

information contained in this manual.

4.2 Composite Structure Antenna Installation General Guidelines:

Composite Aircraft

Before starting installations, always consider with composites that airframe modifications are totally

dependent on the type of construction used in aircraft manufacture. Carbon fiber will have one type of

instructions, Kevlar another, Honeycomb another, etc. Before starting modification refer to included

design data (referenced within) and the list of SAE documents specified below for additional guidance on

a given aircraft type. Also refer to the aircraft manufacturers Maintenance Manual, Aircraft Standard

Practices and/or Structural Repair Manual whenever there is a conflict between listed documents. Design

drawing requirements always take precedent over all other documents. Any area not covered must be

referred to FFS engineering for disposition.

Industry Guidance supplementing design data

SAE ARP 5089 Composite Repair NDT/NDI Handbook

SAE ARP 4916 Masking and Cleaning of Epoxy and Polyester Matrix Thermosetting Composite

Materials

SAE AIR 4844B Composites and Metal Bonding Glossary

SAE AIR 4938 Composite and Bonded Structure Technician/Specialist: Training Document

SAE AIR 5278 Composite and Bonded Structure Engineers: Training Document

SAE AIR 5279 Composite and Bonded Structure Inspector: Training Document

SAE AIR 5719 Teaching Points for an Awareness Class on "Critical Issues in Composite Maintenance

and Repair

SAE ARP 4977 Drying of Thermosetting Composite Materials

SAE ARP 4991A Core Restoration of Thermosetting Composite Components

SAE ARP 5143 Vacuum Bagging of Thermosetting Composite Repairs

SAE ARP 5144 Heat Application for Thermosetting Resin Curing

SAE ARP 5256 Mixing Resins, Adhesives and Potting Compounds

SAE ARP 5319 Impregnation of Dry Fabric and Ply Lay-Up

SAE ARP 5605 Solid Composite Laminate NDI Reference Standards

SAE ARP 5606 Composite Honeycomb NDI Reference Standards

Design data are listed on STC master data list and also referenced within this document. In general, for

nonstructural locations on composite skins each of the maintenance instructions for drilling, sealing, and

ensuring compatible materials for each aircraft must be followed. Galvanic corrosion must be considered

to prevent carbon composites from being in contact with aluminum.

It is preferred that a protective ply of inert cloth such and fiberglass or Kelvar should be cured between

the carbon and aluminum components and properly sealed. If the aluminum is applied directly to a

carbon component all aluminum parts must be anodized per MIL-A-8625, Type II and the external

surfaces of both aluminum and carbon parts use MIL-F-18264, with two coats of epoxy primer per MIL-

P-85582, and two coats polyurethane enamel per MIL-C-83286.

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Fasteners used with carbon must be titanium or corrosion resistant steel. Cadmium-plated fasteners may

not be used in carbon composites. All fasteners should be installed wet with a corrosion inhibiting

sealant. Proper use of backing plates and fastener torque must be considered to prevent damage to the

composite during installation.

During installation, electrical bonding for EMI, HIRF, Lightning aspects (bonding/grounding/routing)

must be complied with as defined on design data.

For fabric aircraft, the GPS antenna may be located under the fabric and mounted to a bracket that is

clamped to the tube structure. The thickness of the support bracket must be determined by the span

between the tubes but may not be less than 0.032 inch thick 2024-T3 aluminum. For fabric that must be

penetrated reinforced fabric gussets or grommets must be used depending on the type of fabric. Care

must be taken to properly seal the area for proper UV considerations.

4.3 Pressurized Structure Antenna Installation General Guidelines:

Pressurized Aircraft

Note: When dealing with pressurized fuselages the procedure in the aircraft Maintenance Manual,

Aircraft Standard Practices, or Structural Repair Manual from the OEM are to be complied with for all

drilling, cutting, sealing and other processes. General practices for installation procedures are described in

AC43.13-2A Chapter 3, Paragraph 44 for the fuselage and AC43.13-2A Chapter 13 for cables penetration

a pressurized structure. In all cases the design drawing will take precedent over all other referenced

documents. If required, specific instructions for initial and future inspections will be in the Instruction for

Continued Airworthiness.

In general, installations on pressurized aircraft must consider not only static strength but all fatigue and

damage tolerance requirements for each type of aircraft and location on the aircraft. Skin thickness,

antenna location, fastener and feed through size, drag and handling loads all must be considered in the

design, analysis, and approval. Proper inspection instructions for inspection method and time between

inspections must be added in the Instructions for Continued Airworthiness for each antenna location on a

pressurized aircraft. This applies to not only the antenna location but to any area where the pressure

vessel requires a penetration for wiring or any other reason. Only approved connectors may be used and

each location will require adequate structural design data for fatigue and damage tolerance (see below).

4.4 GPS Antenna Mechanical Installation

Refer to FreeFlight Systems Antenna Installation drawing number CS-0103-ANT.

4.5 Upper L-Band Antenna Mechanical Installation


4.6 Lower L-Band Antenna Mechanical Installation


4.7 Optional Altitude Digitizer Mechanical Installation

Refer to FreeFlight Systems Equipment Installation drawing number CS-0103-SEN.

ADS-B Control Panel Mechanical Installation


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4.8 ADS-B Control Panel Mechanical Installation


4.9 ADS-B Equipment Mechanical Installation


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5 Accomplishment Instructions – Electrical

5.1 FDL-978 Series Wiring Installation

The FDL-978 Series wiring installation consists of several interface choices that are to be determined by

the installer based on the existing equipment in the aircraft. Upon verification of the existing equipment

the installer should decide based on the wiring diagram CS-0103-WD which installation(s) are required

for his particular aircraft being modified.

There are several options available to the installer to choose from and the wiring diagram is laid out in

such a way as to allow the installer to interface the FDL-978 Series with the aircraft’s existing equipment.

Starting with the FDL-978 Series there are two options to consider, one with an internal GPS receiver

(and optionally an internal transponder monitor function), and one without an internal GPS receiver

which requires a GPS/WAAS 1201 GPS receiver.

There are several optional installations the installer can select based upon the existing aircraft equipment

package. These options are listed below:

WI-FI module.

FTM-190C Remote Transponder Monitor (or FDL-978 with internal transponder monitor

function) for use when the existing transponder does not support remote ADS-B UAT control

modes. It is always recommended to use FDL-978 Series with internal transponder monitor

function instead of the FTM-190C Remote Transponder Monitor if possible.

Trans-Cal Altitude Encoder for use when the existing equipment does not support an RS-232

altitude data output.

External GPS/WAAS such as the GPS/WAAS 1201 GPS receiver for use when the installer

installs the FDL-978 Series without an internal GPS receiver.

TC978 ADS-B controller.

5.2 Wiring diagram & Equip Installation on Equip Shelf Assy

1. Obtain the UAT Equipment Assembly.

2. Install and secure the ADS-B wiring per routing drawing CS0103-WD and CS-0103-RT.

3. Obtain the following equipment:

a. FDL-978 Series UAT part number 87098-00-FX00 or 87098-10-FX10, or 87098-00-

FR00 or 87098-10-FR10 as applicable.

b. FTM-190C XPDR Monitor part number 86930-00-101A. (if used)

c. 1201 GPS/WAAS Sensor part number 84100-03-0304. Used with FDL-978-XVR

part number 87098-10-FX10 or FDL-978-RX part number 87098-10-FR10.

4. Install the equipment on the UAT Equipment Assembly.

5.3 Main Wiring Diagram Installation

1. Obtain the electrical wiring details as shown on drawing CS-0103-WD.

2. Terminate the wiring for the FDL-978 Series connector P1XVR1 as shown on drawing

CS-0103-WD.

3. Route the FDL-978 Series wiring from the UAT equipment assembly to the selected

components for the applicable installation per routing drawing CS-0103-RT.

4. Secure the electrical wiring as shown on drawing CS-0103-RT and CS-0103-WD.

5. Terminate the wiring at ground studs.

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NOTE: Design data includes notes referencing SAE and other guidance documents.

It is important that ALL notes be followed as much of the design guidance is

contained by reference to sections of these documents.

6. Verify point to point wiring continuity and pin to pin isolation per wiring diagram.

5.3.1 Aircraft Power Wiring Installation

1. Route the power wiring as shown on drawing CS-0103-RT to the appropriate destination,

either the circuit breaker panel or the existing GDL 90 mounting tray.

2. Terminate the wiring as shown on drawing CS-0103-WD to the selected interface point.


5.3.2 FDL-978 Series Control Wiring Installation

1. Route the control wiring as shown on drawing CS-0103-RT to the appropriate

destination, either the existing GDL 90 mounting tray, or one of the other control sources

identified on the wiring diagram.

2. Terminate the wiring as shown on drawing CS-0103-WD to the selected interface point.


5.3.3 TC978 Controller Wiring Installation

1. Route the TC978 controller wiring as shown on drawing CS-0103-RT to the desired

location in the aircraft.

2. Terminate the wiring as shown on drawing CS-0103-WD at connector P1TC1.

3. Route TC978 controller wiring to FDL-978 or existing GDL 90 mounting tray and

terminate wiring as shown on the mounting tray side of the referenced connector.


5.3.4 FTM-190C Transponder Monitor Wiring Installation

1. If FTM-190C is installed, route the monitor wiring as shown on drawing CS-0103-RT to

the desired location in the aircraft.

2. Terminate the wiring as shown on drawing CS-0103-WD at connector P1WF1.


5.3.5 WI-FI Wiring Installation

1. Route the WI-FI wiring as shown on drawing CS-0103-RT.

2. Terminate the WI-FI wiring as shown on the wiring diagram.


5.3.6 GPS/WAAS 1201 Wiring Installation

1. If installed, route the 1201 wiring as shown on drawing CS-0103-RT.

2. Terminate the wiring at connector P1GPS.

3. Route the power wiring from connector P1GPS to the circuit breaker panel and terminate

as shown on drawing CS-0103-WD.


5.3.7 Air/Ground Discrete Wiring Installation

1. Route the Air/Gnd discrete wiring as shown on drawing CS-0103-RT to the appropriate

destination, either the existing GDL 90 mounting tray or the aircraft’s weight on wheels

system.

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2. Terminate wiring as shown on drawing CS-0103-WD at the selected location.


5.3.8 L-Band Suppression Wiring Installation

1. Route the L-band suppression wiring as shown on drawing CS-0103-RT to the

appropriate destination, either the existing GDL 90 mounting tray or the existing

aircraft’s transponder.



5.3.9 ADS-B Status Annunciator

1. If installed, route the ADS-B annunciator wiring as shown on drawing CS-0103-RT to

the desired location in the aircraft.



5.3.10 FDL-978-XVR ARINC 429 Wiring Installation

1. Route the 429 wiring as shown on drawing CS-0103-RT.

2. Terminate the 429 wiring as shown on drawing CS-0103-WD at either the existing GDL

90 mounting tray or one of the optional interfaces shown on the drawing.


5.3.11 FDL-978-Series RF Cable Terminations (Ref Fig 1)

1. Obtain the ADS-B coax cables as shown on drawing CS-0103-WD.

2. Identify the coax cables as shown on drawing CS-0103-WD.

3. Install and secure the coax cables per drawing number CS-0103-RT.

The coax cables shall not be located near flight control cables and controls, high

electrical capacity lines or fuel lines.

The coax cables shall be located in a protected part of the aircraft.

Do not route near high energy sources.

4. Terminate FDL-978 Series connector GPS, onto the GPS antenna coax cable.

5. Verify continuity and isolation per wiring diagram.

6. Terminate FDL-978 Series connector TOP, onto the UAT TOP antenna coax cable.


8. Terminate FDL-978 Series connector BOT, onto the UAT BOT antenna coax cable.


10. Terminate GPS/WAAS 1201 connector P2GPS onto the GPS antenna coax cable, if

required.


12. Terminate FTM-190C connector P2RX1 onto the transponder monitor antenna coax

cable, if required. 13. Verify continuity and isolation per wiring diagram.

14. Route terminated coax cables to selected installation destination.

15. Terminate coax cables at either the existing GDL 90 mounting tray or the alternate

location shown in the drawing CS-0103-WD.

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5.4 Circuit Breaker Panel Modification

1. If not already available, obtain the 2 amp ADS-B circuit breaker, the 2 amp GPS circuit

breaker and the 1 amp ALT ENCODER circuit breaker and install into the circuit breaker

panel.

2. Identify the circuit breakers as shown on drawing CS-0103-WD, flag note 10.

3. Terminate the bus wiring to the circuit breakers as shown on drawing CS-0103-WD, flag

note 26.


5.5 Optional Altitude Digitizer Electrical Installation

1. Terminate the wiring at connector P2ALT as shown on drawing CS-0103-WD.


5.6 Altitude Reporting Equipment Interface

1. If the optional altitude digitizer is not installed terminate the following wires into the

altitude reporting equipment source as shown on drawing CS-0103-WD.


5.7 System Continuity and Isolation Test

Upon completion of all the FDL-978 Series ADS-B system wiring installation perform a complete end to

end continuity check of the newly ADS-B system wiring using a Simpson 260 volt-ohmmeter, or

equivalent set on “0” scale of all wiring, including a check of all ADS-B system wiring to aircraft ground

and shorts between pins.

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6 Installation Outline for GDL-90 Replacement

6.1 Assemble the QCR for GDL-90 Replacement

1. Unbox the QCR.

2. Unbox the FDL-978 and note the serial number in the AFMS.

3. If a TC-978 is to be used, unbox the TC-978.

4. Remove the 6 screw holding the side panel on the QCR.

5. Cut the zip-tie holding the Harness to the QCR.

6. Remove the installation kit from the inside of the QCR.

7. Locate the package of 6 nuts and mount the FDL-978 to the embedded studs on the inside of the

QCR. Secure the FDL-978 with these nuts.

8. Connect the 44-pin connector with two 4x40 0.20” screws.

9. Connect the RF cables to the FDL-978:

a. The top and bottom UAT antennas are located on a vertical line on the left side of the

QCR while looking in from the outside, standing the QCR on smaller side. The top

antenna is on top.

b. The top antenna connector on the FDL-978 is on the far right side when looking head-on

at the 44-pin connector.

c. The GPS antenna connector is the center connector on the FDL-978.

d. The bottom UAT connector is the remaining connector on the far right.

e. The GPS antenna on the QCR is the remaining connector.

10. If standoffs are not already installed on the hybrid connector on the QCR facing the outside,

remove the 2 flat-head 4x40 screws holding the hybrid connector into the QCR. Reinstall the

hybrid connector using the standoff kit (FFS PN 87703) such that the standoffs face the outside of

the QCR.

6.2 GDL-90 Replacement – Quick Change Rack (QCR)

1. Remove the GDL-90 and set aside for shipment destination for disposal.

2. Remove existing 15-pin connector. Examine connector and pins for damage. Replace as

appropriate.

3. Remove existing 37-pin connector. Examine connector and pins for damage. Replace as

appropriate.

4. If the TC-978 is to be installed:

a. Run the wires from the QCR to the front panel in the aircraft.

b. Mount the TC-978 using the included install kit with an existing standard 2 ¼” hole in the

front panel.

c. Install the wires from the front panel into the hybrid connector that mates to the QCR hybrid

connector.

d. Verify connections by ringing-out the new wires.

5. Accommodating the Hybrid (Remote-on or TC-978) connector in the GDL-90 tray options:

a. Option 1: Installing the hybrid connector 3-plate capture solution.

i. Remove the 3-plate capture solution parts from the packaging

ii. In the hybrid connector and the 3-plate capture solution using drawing 87420-00.

Capstone-II-0103


b. Option 2: Modify the fan-hole on the GDL-90 tray to accommodate the hybrid connector

pass-through.

i. Remove RF cables from the tray and mark the locations. Examine connector and

pins for damage. Replace as appropriate.

ii. Remove the tray from the aircraft.

iii. In order to accommodate the hybrid connector while maintaining the ability to

remove and replace the QCR after installation without needing to disconnect

cables: With a grinding tool, enlarge the fan-hole on the tray. Using part # 87414

as a guide, remove approximately 1/8” of material from the top and bottom of the

opening. De-bur the machined opening. Clean opening. Replace the rack in the

aircraft. Replace the RF cables in the original locations.

6. Determine location of the wires connecting to the altitude encoder in either the 15-pin connector

or the 37-pin connector. This may require the installer to verify the connections by ringing-out the

wires.

7. Move altitude encoder input connections to the appropriate locations on the 37-pin connector for

port 4 on the QCR.

8. Determine the location of the wires connecting to the MFD. This may require the installer to

verify the connections by ringing-out the wires.

9. Move the MFD connections to the appropriate connections on the 37-pin connector for port 6

(RS422 Port) on the QCR.

10. Determine the location of the wires connecting to the transponder or control head for the GDL-

90. This may require the installer to verify the connections by ringing-out the wires.

11. Move the transponder connections to the appropriate connections on the 15-pin connector for port

2 on the QCR.

12. Remove GDL-90 personality module and discard.

13. Install FDL-978 personality module into the 15-pin connector.

14. Reserved

15. Run and mark the wires for the Air/Ground discrete if installed.

16. Run and mark the wires for the L-Band Suppression Wiring.

17. Run and mark the wires for the separate ADS-B annunciator if installed.

18. Install the QCR into the rack in the aircraft and secure the dzus fastener.

19. If not TC-978 is installed and the maintenance interface is not being used to configure the FDL-

978, connect the configuration cable (FFS PN 87682-00 Rev B or later) to the hybrid connector

on the QCR through the enlarged fan hole opening in the rack. Attach the TC-978 to the

configuration cable and continue with the Configuration with TC-978 section.

20. If the maintenance port 5 interface is to be used for configuration, connect the maintenance port

interface connection cable (FFS PN 86971-00-2) to the FDL-978. Connect the other end of the

maintenance port interface cable a PC running a terminal program such as Tera Term. Follow the

configuration procedure listed in the FDL-978 Series Installation Manual 87343 current revision.

21. If the maintenance port 3 interface is to be used for configuration, connect the RS232 serial port

connections to a RS232 to USB converter. Connect the USB converter to a PC running a terminal

program such as Tera Term. Follow the configuration procedure listed in the FDL-978 Series

Installation Manual 87343 current revision. Note: The RS232 connections for port 3 cannot be

Capstone-II-0103


used with a TC-978 control head attached to the system. Also, the REMOTE-ON pin on the 44-

pin connector must be grounded for the system to power-on.

6.3 Installation without QCR

1. Remove Interior pieces for installation

a. Carefully remove and inspect only what is necessary to remove old equipment and install

new equipment.

2. Remove old equipment to be replaced during this installation.

3. Carefully tag or mark cables and wires that are to be reused. Examine connector and pins for

damage. Replace as appropriate.

4. Unbox the FDL-978 and note the serial number.

5. If a TC-978 is to be used, unbox the TC-978.

6. If new antennas are to be installed on the aircraft, then unbox the antenna(s).

a. Install the UAT antenna(s) on the aircraft. If this is a single antenna install, install only

the bottom antenna.

7. Run and mark the RF cable(s) to the FDL-978 install location in the aircraft.

8. Install the GPS WAAS antenna on the top of the aircraft so that it cannot be obstructed from the

sky during normal flight.

9. Run and mark the GPS cable to the FDL-978 install location in the aircraft.

10. Run and mark the wires for aircraft power and aircraft ground separately from the data wires for

the FDL-978.

11. Attach the aircraft power (10 – 40 Volts) through a 2 Amp breaker to the FDL-978.

12. If a TC-978 is to be installed, run the wires to the front panel of the aircraft.

13. If a TC-978 is to be connected to the static pressure system on the aircraft, use the installation kit

provided with the TC-978 and follow all applicable airworthiness provisions for the aircraft. The

static system should be checked for leaks if a device or fitting has been added or removed from

the line.

14. Run and mark the wires for external sensors such as Altitude input and control.

15. Run and mark the wires for the MFD or Wi-Fi module if installed.

16. Run and mark the wires for the Air/Ground discrete if installed.

17. Run and mark the wires for the L-Band Suppression Wiring.

18. Run and mark the wires for the separate ADS-B annunciator if installed.

19. Verify all wires by ringing them out.

20. Pin the wires into the appropriate locations on the 44-pin FDL-978 connector.

21. If no TC-978 is to be installed, the “Remote-On” pin on the FDL-978 must be grounded for the

unit to power-on. This can be accomplished by tying that pin on the connector to a ground pin.

22. Install the PM into the 44-pin connector and attach to the back-shell for the connector.

23. Mount the FDL-978 to secure location in the aircraft such as a bulk-head or avionics shelf. Do not

mount the unit directly to the aircraft skin.

24. Connect the 44-pin connector to the FDL-978.

25. Connect the RF cables to the FDL-978 in this order from the right side of the FDL-978 in a

normal upright position: Top UAT antenna (as applicable), GPS WAAS antenna, Bottom UAT

antenna.

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26. If the maintenance port 5 interface is to be used for configuration, connect the maintenance port

interface connection cable (FFS PN 86971-00-2) to the FDL-978. Connect the other end of the

maintenance port interface cable a PC running a terminal program such as Tera Term. Follow the

configuration procedure listed in the FDL-978 Installation Manual 87343 current revision.

27. If the maintenance port 3 interface is to be used for configuration, connect the RS232 serial port

connections to a RS232 to USB converter. Connect the USB converter to a PC running a terminal

program such as Tera Term. Follow the configuration procedure listed in the FDL-978

Installation Manual 87343 current revision. Note: The RS232 connections for port 3 cannot be

used with a TC-978 control head attached to the system. Also, the REMOTE-ON pin on the 44-

pin connector must be grounded for the system to power-on.

6.4 Configuration with TC-978

1. Ensure the TC-978 is in the “OFF” position and apply power to aircraft instruments.

2. Turn the TC-978 power knob to “ALT”. Ensure that the FDL-978 lights are flashing. Verify that

the TC-978 is powered and proceeding through the startup cycle.

3. Restart the FDL-978 in configuration mode by holding the “FN” key down while turning the

knob from off to “ALT”.

4. Configure the FDL-978. Cycle power on the FDL-978.

7 Preservation of Previous Systems

It is the installer’s responsibility to preserve the essential characteristic of the aircraft being modified

by this manual to be in accordance with the aircraft manufacturer’s original design. This includes the

preservation of multiple power buses, which reduce the probability of interrupting power to essential

instruments and avionics.

Capstone-II-0103


8 Equipment Operational/Functional Test

8.1 Preliminary Checkout

Upon completion of the installation, wiring point to point ring out and equipment installation ready

the aircraft for System Configuration (including CDTI if installed) and Checkout. Observe all safety

precautions in readying the aircraft for checkout. When all of the safety issues have been addressed

and all installation issues are resolved begin system preliminary checkout as defined in the FDL-978

Series Installation Manual (P/N 87343 current revision) section titled, “Preliminary Checkout”.

8.2 Installation Setup and Configuration

Upon completion of the Preliminary Checkout and correction of all discrepancies noted, begin the

Installation Setup and Configuration. Refer to the FDL-978 Series Installation Manual (P/N 87343

current revision) section titled, “Installation Setup and Configuration”. In Installations where a

TC978 is not installed, a spare TC978 along with the RCEP Configuration Cable (P/N 87417-00 Rev

A or later approved revision) maybe temporarily connected to the hybrid connector (P3MT1 on the

Quick Change Rack Assembly) where the Remote-On (P/N 87419-00 Rev A or later approved

revision) connector is mounted. This allows the RANGR to be configured using the TC978. Once

configuration is complete, remove the RCEP Configuration Cable and replace the Remote-On

connector to complete the installation.

The FDL-978 Series and CDTI if installed must be properly configured prior to performing system

functional checkouts. When configured correctly, the FDL-978 Series will annunciate failures that are

detected with interfacing systems when it is first turned on. Correct any annunciated failures prior to

proceeding with the ground checks.

The following are required configurations when a Garmin Position source is used:

87098-10 [ ] Configurations

ICAO Address As required

VFR Call Sign As required

GPS Configuration Level C

NACv Mode Auto (from GPS)

Receiver Config no1090, 978

Emit Category Light AIRCRAFT

Squat Mode As required

Groundspeed Threshold 30 knots

Vehicle Size As required

UAT Ant bottom, No DC Gnd Chk

GPS Ant Offset As required

Mode A Rx Disable

Disable Squawk Tx Off

Max Targets max

Chelton CSA Enable disable

Traffic Vel Validation enable

Serial In 1

The Serial input from the Garmin Position Source must be set to

ADS-BPLUS, 9600

Capstone-II-0103


Serial Out 1 UNUSED, 9600 or as required

Serial In 2 As required

Serial Out 2 As required

Serial In 3 As required

Serial Out 3 As required

Serial In 4 Alt-Encoder, 9600 or as required

Serial In 5 Disp-Ctrl, 115200 or as required

Serial Out 5 Traffic-Alert, 115200 or as required

Serial In 6 UNUSED, 9600

Serial Out 6 UNUSED, 9600

ARINC In 1 UNUSED, low

ARINC IN 2 UNUSED, low

ARINC Out 1 UNUSED, low

8.2.1 System Checkout – Power on Self-Test (POST)

The FDL-978 Series executes a POST at power-up to verify the unit operation as well as other internal

functions. Failures and system status are recorded and communicated via four LEDs in the front of

the unit.

8.3 FT-9000 Ramp Tester Initial Installation Checkout

After completing initial installation of the ADS-B system, it is necessary to verify the functionality of

the system using the FT-9000 Ramp Tester. The FT-9000 system includes the Ramp Tester unit along

with an Android tablet with the FT-9000 Ramp Tester application installed. The instruction manual for

the system is installed on the Android tablet.

The Ramp Tester system allows the installer to verify the correct installation and configuration of the

system as well as the external sensors supplying data to the FDL-978. The Ramp Tester system will

parse the output messages from the ADS-B system, that could indicate problems with configuration,

data connections, or RF connections to and from the system.

8.3.1 RCEP Post Installation Procedure

1. Verify FDL-978 control.

2. Using the FT-9000 Ramp Tester:

a. Verify that the configuration settings are correct for the aircraft.

b. Verify changes in squawk and Ident using the controlling device for the FDL-978.

c. Verify that the Altitude displayed on the TC-978 is the same as the transponder, if

equipped.

d. Verify that the MFD is receiving data from the FDL-978.

e. Verify the GPS position.

f. Verify that NIC is 7 or better and that NACp is 8 or better, after the GPS has obtained the

local almanac if necessary and allowed at least 2 minutes for acquisition on a clear day

with an unobstructed view.

3. Power off the FDL-978 and the aircraft.

Capstone-II-0103


4. If a remote-on connector is to be installed:

a. Remove the configuration cable from the back of the QCR.

b. Remove the QCR from the aircraft.

c. Install the remote-on connector to the hybrid connector on the back of the QCR.

d. Replace the QCR in the aircraft and secure the dzus fastener.

e. Re-verify control, traffic output data, altitude, and GPS data using FFS FT-9000 Ramp

Tester.

5. Complete all applicable paperwork for the installation such as the Log book entries and 337

forms.

Capstone-II-0103


9 GPS / VHF Comm Interference Check

Following configuration of the PM and the aircraft, the aircraft should be moved to a location with

an unobstructed view of the available GPS satellites.

Check the GPS operation as follows:

1. Refer to the FDL-978 Series Installation Manual Section X Transceiver Maintenance Adapter.

2. A special Series USB to Serial Adapter Module (P/N 86971-00-2) is required to connect the

FDL-978 Series Maintenance port to a Personal Computer (PC) for the purpose of configuring

the system with a terminal program such as TeraTerm.exe. Interconnect diagrams of the USB

Serial Adapter and Cable are shown on page X-1 of the referenced installation manual.

3. Turn on the FDL-978 and allow the unit to acquire a position. Turn off all other avionics.

4. Verify that the GPS LED on the front of the FDL-978 Series stops blinking and remains

steadily lit within 20 minutes of power-on, indicating unit has acquired a GPS position.

5. Turn on other avionics one at a time and verify that the GPS status LED remains steady on.

6. Check for VHF comm transmitter interference as follows:

The VHF interference check must be completed on all installations.

a) Tune the Com 1 radio to 121.125 MHz. Listen on the frequency to ensure it is not in

use, and then transmit for 30 seconds.

b) While transmitting, observe the GPS LED. Verify that the GPS LED remains steady on.

If not, additional isolation measures must be taken to resolve the interference.

Capstone-II-0103


10 Construction & Validation of Structures

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 FDL-978 Series mounting tray.

Baggage compartments and cabins or cockpit floors are good mounting platforms

providing 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 AC43.13-2B Chapter 1

to verify that it is capable of supporting the required loads.

The FDL-978 Series installation must be capable of withstanding the Ultimate Load

Factors listed in Table 6 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.

Since the combined weight of the FDL-978 Series and its equipment mounting rack

is 6.4 lbs, the static loads which must be applied (Load Factor x 6.4 lbs.) will be the

following:

Table 6 - Static Test Load

Direction of Force

Load Factor

Static Test Load

(Load Factor x FDL-978 Series wt)

Downward 6.6 g (6.6 x 6.4) = 42.24 lbs

Upward 6.0 g (6.0 x 6.4) = 38.4 lbs

Sideward 4.5 g (4.5 x 6.4) = 28.8 lbs

Forward 18.0 g (18.0 x 6.4) = 115.2 lbs

One method of determining the static load capability is as follows:

1. Mark and drill the holes where the FDL-978 Series equipment rack will be mounted.

2. Install four 8-32 machine screws (MS35206, AN526 or equivalent) in the four

holes which will be used to mount the FDL-978 Series equipment rack using

washers, nuts and nut plates to mount the equipment rack to the mounting surface.

Note: some means of locking fastener must be used, i.e. lock nuts & lock washers.

Capstone-II-0103


3. For testing downward loading, place shot bags or other suitable weights totaling

42.24 pounds within the footprint outlined by the four screw holes (assuming the

mounting surface is horizontal) or use a calibrated force gauge at the location of the

center of gravity when the unit is mounted.

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 150 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 above calculated forces (i.e. 38.4 lb upward, 28.8 lb sideward and

115.2 lb forward).

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 which 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 FDL-978 Series equipment rack may

be permanently mounted on it.

Capstone-II-0103


11 Documentation Required After Installation Completion

The following must be accomplished prior to recording completion of the FreeFlight STC as

required by regulation.

11.1 Instructions for Continued Airworthiness Modification for any Interfacing

Component

Affix an adhesive label with the following statement to the cover of the Instructions for Continued

Airworthiness for any interfacing component:

“Any design changes to this equipment must consider the continued airworthiness of the ADS-B

system. This label must be transferred to future ICA revisions.”

11.2 Instructions for Continued Airworthiness Modification If an External (non-

FreeFlight) GPS is Used as a Position Source

Modify the Removal and Replacement ICA instructions in the GPS maintenance manual to include the

following statement:

“Removal and replacement of the GPS receiver also requires a full functional check of the

ADS-B system per FreeFlight Systems INSTRUCTIONS FOR CONTINUED

AIRWORTHINESS For APPROVED MODEL LIST For ADS-B SYSTEM Installed in

Approved Model List Aircraft Report No. Capstone-ICA-0103 Revision B-1 or later, in

the Interface/System Functional Testing section. Make a log book entry for accomplishment

of this test.”

The requirement can be accomplished by affixing an adhesive label with this statement adjacent to or

above the Removal and Replacement ICA instructions.

11.3 Instructions for Continued Airworthiness Completion Instructions

a. Complete the Installed Equipment List Table.

b. Prepare and insert a Wiring Diagram titled, “Wiring Diagram for (insert the serial number and

Registration Number of the airplane)” for the FreeFlight ADS-B Modification for the

modification to this airplane here.

c. Insert a drawing after the wiring diagram depicting the locations of the Installed Equipment titled,

“Installed Equipment Locations for (insert the serial number and Registration Number of the

airplane)” for the modification to this airplane.

Capstone-II-0103


Place the Completed ICA in the Airplane Permanent Maintenance Records with the Continued

Airworthiness Instructions for the Airplane.

11.4 Airplane Flight Manual Supplement Completion Instructions

Step 1:

Obtain the AFMS by emailing [email protected] and requesting the document.

Once obtained, print the document. The printing must meet the following criteria:

The document must be of a type that is not easily erased, disfigured, or misplaced, and is capable

of being inserted in a manual provided by the airplane operator, or in a folder, or in any other

permanent binder.

Step 2:

Using black ink, fill in the registration number and the serial number of the airplane on page 1:

FAA APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT

or

SUPPLEMENTAL FLIGHT MANUAL

For

FreeFlight Systems

87098- (FDL-978-) Series ADS-B Systems

REGISTRATION No: ________________

SERIAL No.: ________________

Step 3: Fill in the Installed equipment Table in the AFMS. Using black ink, place a check mark

to identify the type of system installed and the equipment interfaces. Place the completed

Airplane Flight Manual Supplement in the airplane to be included in the documents required to

be in the airplane.

Block by block instructions:

Capstone-II-0103


This is a reproduction if Table 2 in the AFMS. The instructions for each block are found in

[Bold and Italics] in the left column.

ADS-B (UAT) System

The ADS-B (UAT) type installed in

this Airplane:

Using black ink, check mark the system

type; ADS-B OUT, ADS-B IN or both.

The Installed ADS-B (UAT) Equipment Installed in this Airplane and

Type of System:

ADS-B Type:

ADS-B OUT

ADS-B IN

ADS-B IN and OUT

The installed ADS-B OUT system (if installed) has been shown to meet the equipment requirements of 14

CFR 91.227.

Peripheral Device For ADS-B OUT Peripheral Device Installed in this Airplane:

1.

Dedicated ADS-B OUT UAT

Controller for Airplanes

Without an Onboard 1090MHz

Transponder:

[This block is for airplanes

that have no transponder and

ADS-B OUT is installed. If

this is an ADS-B OUT system

with no transponder installed

(this is not common), select

and mark the type of dedicated

ADS-B OUT controller that is

installed in this airplane. If

the airplane has a transponder

or the installation is ADS-B IN

only, then check the “Not

Available” box.]

Dedicated ADS-B OUT UAT Controller Installed in this

Airplane:

FreeFlight Systems TC-978 UAT Controller

Aspen EFD1000 PFD

Garmin MX20 MFD

Garmin GMX 200 MFD

Garmin GSL 71 UAT Control Panel

Not Available

2.

Separate ADS-B OUT UAT

Controller used for Temporary

Control where the non-digital

Transponder is Not Interrogated

by a Ground Station:

[If this airplane has a non-

digital transponder (such as a

KT-76A), then one of these

blocks must be checked. Select

and mark the type of ADS-B

OUT UAT controller that is

installed in this airplane. If a

digital transponder is installed

and a controller is not

ADS-B OUT UAT Controller Installed in this Airplane:


Aspen EFD1000 PFD

None - The UAT is always controlled

simultaneously by the digital onboard transponder.

Not Available

Capstone-II-0103


Peripheral Device For ADS-B OUT Peripheral Device Installed in this Airplane:

required, check “None”. If

ADS-B IN only is installed,

check the “Not available”

box.]

3.

ADS-B OUT UAT Annunciator

Type:

[If ADS-B OUT (or both ADS-

B IN and OUT) is installed in

this airplane, then one of these

blocks checked. Select and

mark the annunciator type that

is installed in this airplane. If

ADS-B IN only is installed,


box.]

ADS-B OUT UAT Annunciator Type Installed in this Airplane:


Aspen EFD1000 PFD

Garmin MX20 MFD

Garmin GMX 200 MFD

Chelton FlightLogic EFIS

Panel Annunciator (“ADS-B” in amber)

Not Available

Capstone-II-0103


Table 2 Installed Equipment List, continued

Peripheral Device for ADS-B IN Peripheral Device Installed in this Airplane:

4.

ADS-B IN Traffic and FIS-B

Display:

[If ADS-B IN (or both ADS-B

IN and OUT) is installed in


blocks must be checked. Select

and mark the ADS-B IN

display that is installed in this

airplane. If ADS-B OUT only

is installed, check the “Not

available” box.]

Traffic and FIS-B Display Installed in this Airplane:

Aspen EFD1000 PFD

Aspen EFD1000 MFD

Aspen EFD500 MFD

Garmin MX20 MFD

Garmin GMX 200 MFD


None - Wi-Fi Module only

Not Available

5.

ADS-B IN Traffic Only

(Proximity Traffic’ and ‘Other

Traffic’ symbols. There are no

Traffic Alerts)

[If ADS-B IN (or both ADS-B

IN and OUT) is installed in


blocks must be checked.

Garmin ADS-B IN (Traffic Only) Installed in this Airplane

Garmin 400W/500W Series System #1


Not Installed

6.

Wi-Fi Module:

(used with ADS-B IN)

[If the Wi-Fi module is

installed in association with

the ADS-B IN (or both ADS-B

IN and OUT) system, then

check the “Installed” box. If

ADS-B IN is installed but

there is no Wi-Fi, then check

the “Not installed” box. If

only ADS-B OUT is installed,


box.]

FreeFlight Wi-Fi Module Installed in this Airplane:

Installed

Not installed

Not available

Capstone-II-0103


Peripheral Device for ADS-B IN,

ADS-B OUT or both Peripheral Device Installed in this Airplane:

7.

External GPS Type:

[Check the applicable box

corresponding to the

installation in the airplane]

ADS-B IN and/or OUT External GPS Type Installed in this

Airplane:

FreeFlight Systems Model 1201 GPS

Garmin 400W/500W Series GPS #1


None (internal GPS)

8.

Air-Ground Status

Determination

[Check the applicable box

corresponding to the

installation in the airplane.]

ADS-B IN and/or OUT Air-Ground Status Determination on this

Airplane:

Discrete signal using airspeed

Discrete signal using weight-on wheels

Determined internally in the FreeFlight System

Capstone-ELA-0103Merrill Field Instruments 940 Merrill Field Dr. Anchorage Alaska 99501

Rev A Page 1 of 10

Electrical Load Analysis

for the

FreeFlight Systems

“Automatic Dependent Surveillance-Broadcast” (ADS-B)

installed in

Model listed in an

Approved Model List (AML) STC

Report No: Capstone-ELA-0103

Revision: A

Capstone-ELA-0103

Merrill Field Instruments 940 Merrill Field Dr. Anchorage Alaska 99501

Rev A Page 2 of 10

REVISION PAGE

REV DESCRIPTION RELEASED BY DATE

- Initial Release R. Harper 11-27-13

A Updated Paragraph 7.0. to reflect load based on aircraft load test.

R. Harper 02-10-14

Capstone-ELA-0103


Rev A Page 3 of 10

TABLE OF CONTENTS

1.0 PURPOSE .............................................................................................................................................. 4 2.0 REMOVED LOADS ............................................................................................................................... 5 3.0 ADDED LOADS ..................................................................................................................................... 6 4.0 BACKUP BATTERY ............................................................................................................................. 8

5.0 SUMMARY ............................................................................................................................................. 8

6.0 NOTES ................................................................................................................................................... 9 7.0 Cessna 185 Summary .......................................................................................................................... 10

Capstone-ELA-0103


Rev A Page 4 of 10

1.0 PURPOSE

This electrical load statement identifies electrical loads that have been removed or added to aircraft model _________ serial number ______________as a result of an alteration, and allows update of applicable aircraft records. The listed loads are calculated based on the maximum values published in the manufacturer’s technical manuals. This section of document allows installers to access aircraft load changes at the time of follow on STC installations. NOTE: Original STC conformity aircraft load assessment is reflected in section 7.0 of this document. NOTE: Installer shall use this document to assess aircraft electrical system load change by entering existing load information, removed loads, and newly installed equipment load information for candidate aircraft to establish new totals ensuring aircraft power system capacity continued compliance to regulatory requirements. Not all aircraft have all busses shown, when not installed buses should be marked N/A. (Ref FAR 23.1351 (a) (1)) When possible, analysis shall be based solely on the aircraft manufacturer’s electrical loads analysis which is conservative, the actual electrical load will be significantly less than shown. The total loads shown shall be less than 85% of generating system capacity to allow for adequate power margins in operational conditions. (Ref 23.1351 (a) (2)) If no aircraft manufacturer’s electrical loads analysis can be obtained an aircraft power system load test shall be performed and actual load recorded where indicated. (Ref 23.1351 (a) (2))

NOTE: Some candidate aircraft have two engines, each of which has a DC source with capacity rated in continuous and maximum (short term) Amp DC. The two generators are isolated from each other by power system design protection but still operate in parallel under normal conditions. Either engine can drive the electrical system under failure conditions as described in aircraft AFMS. Based on this, the electrical system bus capacity of the primary bus and of total aircraft power capacity must be assessed for impact to insure required power margin is maintained. (Refer to manufacturer’s maintenance manual or aircraft electrical load analysis (if available) for candidate aircraft). Power system evaluation should consider the following: a. Aircraft power system worse case loads (Night Cruise). b. All conditions subject to load shed under basic aircraft manufacturers design. c. Total power system loads under noted condition. d. Total Reserve under worse case loads.

Capstone-ELA-0103


Rev A Page 5 of 10

1.1 LOADS (NEW EQUIPMENT) The following list reflects new equipment loads and should be used for load assessments at each follow on aircraft installation. Loads shown are for individual units (ea).

Nomenclature Model / Part

Number Max Load 14V Aircraft (Amp)

Max Load 28V Aircraft (Amp)

ADS-B Transceiver FDL-978-XVR 0.20 A 0.10 A

Transponder Monitor FTM-190C 0.06 A 0.04 A

GPS/WAAS(if installed) 1201 0.50 A 0.25 A

WI-FI Transceiver 86943-00 0.06 A 0.04 A

Alt Digitizer(If installed) 0.25 A 0.27 A

2.0 REMOVED LOADS

Equipment removed as a result of this alteration is to be listed on the appropriate DC/AC bus by nomenclature, model, part number and manufacturer’s listed load.

2.1 PRIMARY DC BUS




GPS/WAAS receiver / Universal Access Transceiver**

GDL 90 3.0A 1.5A

TOTAL REMOVED LOADS

2.2 SECONDARY DC BUS (If available)




TOTAL REMOVED LOADS

** STC conformity aircraft

Capstone-ELA-0103


Rev A Page 6 of 10

2.3 PRIMARY AC BUS (Inverter 1 Load reflected under DC Bus) (If available)




TOTAL REMOVED LOADS

2.4 SECONDARY AC BUS (Inverter 2 Load reflected under DC Bus) (If available)




TOTAL REMOVED LOADS

3.0 ADDED LOADS

Equipment added as a result of this alteration is to be listed on the appropriate DC bus by nomenclature, part number and manufacturer’s listed load. 3.1 PRIMARY DC BUS (Left DC Bus-Pilots)




TOTAL ADDED LOADS

Capstone-ELA-0103


Rev A Page 7 of 10

3.2 SECONDARY DC BUS (If available)




TOTAL ADDED LOADS

3.3 PRIMARY AC BUS (Inverter 1 Load reflected under DC Bus 1A) (If available)




TOTAL ADDED LOADS

3.4 SECONDARY AC BUS (Inverter 2 Load reflected under DC Bus 2A) (If available)




TOTAL ADDED LOADS

Capstone-ELA-0103


Rev A Page 8 of 10

4.0 BACKUP BATTERY

The following loads reflect equipment, nomenclature and part number for the manufacturer’s listed load connected to the backup battery should the primary DC bus fail.

4.1 BACKUP BATTERY LOADS

Equipment P/N Max load (Amp)

TOTAL BACKUP BATTERY AMPS

5.0 SUMMARY

The existing bus load added to the new bus load less the removed bus load is the new aircraft power system total bus load. If a load test is performed in the absence of an electrical load analysis, enter the results of the test as the NEW LOAD TOTAL.

Primary DC Bus (Amps)

Bus Capacity Note 1 Existing Bus Loads Note 2 or Note 5 Added Bus Loads Remove Bus Loads NEW LOAD TOTAL Note 4

Secondary DC Bus (Amps)

Bus Capacity Note 1 Existing Bus Loads Note 2 or Note 5 Added Bus Loads Remove Bus Loads NEW LOAD TOTAL Note 4

Primary AC Bus (Amps)

Bus Capacity Existing Bus Loads Added Bus Loads Remove Bus Loads NEW LOAD TOTAL

Secondary AC Bus (Amps)

Bus Capacity Existing Bus Loads Added Bus Loads Remove Bus Loads NEW LOAD TOTAL

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Rev A Page 9 of 10

Backup Battery Load (Amps) Battery Type Battery Capacity (AH) Equipment Powered TOTAL BATTERY LOAD

6.0 NOTES

NOTE 1: The electrical bus capacity should be obtained from the aircraft manufacturer specification.

NOTE 2: The existing bus loads should be obtained from the existing aircraft Electrical Load Analysis Report No,______________________ Dated. ____________________

NOTE 3: Aircraft Battery assumes the load of the ADS-B System when the primary DC bus fails.

Formula for calculating aircraft Battery discharge time (Example)

(Battery AH)(60 minutes) (assumed initial state of charge 80%) (Battery Load in Amp) Example: 29.0 x 60 x .8 = 88.00 Min. 12.00

NOTE 4: Where the use of placards or monitoring devices is not practical or desired, and where assurance is needed that the battery in a typical small aircraft generator/battery power source will be charged in flight, the total continuous connected electrical load may be held to approximately 80 percent of the total rated generator output capacity. (When more than one generator is used in parallel, the total rated output is the combined output of the installed, generators.)

When two or more generators are operated in parallel and the total connected system load can exceed the rated output of one generator, provide means for quickly coping with the sudden overloads which can be caused by generator of engine failure. Employ a quick load reduction system or procedure whereby the total load can be reduced to a quantity which is within the rated capacity of the remaining operable generator or generators.

NOTE 5: In the absence of an existing Electrical Load Analysis, an electrical load test shall be

performed. This test shall be in accordance with the aircraft manufacturer’s instructions and the basic aircraft flight manual supplement. This will insure no electrical load limit condition has been exceeded. This test shall be witnessed and the result recorded by appropriate quality control personnel. The recorded load values shall be entered into the aircraft records prior to the aircraft release.

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Rev A Page 10 of 10

7.0 Cessna 185 (STC conformity) Aircraft Load Summary

7.1 Analysis

The alternator for the Primary bus is rated at 60 Amps, 14 V. The total continuous electrical load with all systems on (excluding Landing Lights, Flap Motor, and Landing Gear Motor) is 23.97 Amps Net Result = 40% Maximum continuous load on alternator capacity

Primary DC Bus (Amps) (Worse Case Condition) Bus Capacity 60 A Alternator Rating Existing Bus Loads 38.65A Cruise/Night Added Bus Loads .32A Cruise/Night Remove Bus Loads 3.0A Cruise/Night NEW LOAD TOTAL 35.97 Cruise/Night

Backup Battery Load (Amps) Battery Type Battery Capacity (AH) 29.0 Standard RG-35A, CB-35A Equipment Powered (battery bus total) 35.97 Note 3 TOTAL BATTERY LOAD

7.2 Backup Battery (12V)

Aircraft Battery assumes the load of the ADS-B System when the primary DC bus fails.

Formula for calculating aircraft Battery discharge time (Example)

(Battery AH)(60 minutes) (assumed initial state of charge 80%) (Battery Load in Amp) Result: 29.0 x 60 x .8 = 38.69 Min. 35.97

The above analysis is based on the aircraft manufacturer’s electrical loads analysis and on an actual aircraft loads test. The total load shown is less than 80% of generating system capacity providing for adequate margins in all system operational cases. Battery loads while under alternator failure condition are also shown to comply with regulatory requirements. With AFMS load shed procedure battery capacity can be extended beyond 36 minutes calculated.

Capstone-AML-0103

REPORT No: Capstone-AML-0103

Approved Model List

For

ADS-B System

Installed in

Approved Model List Aircraft

Prepared By: Reviewed: Approved By:

Michael Frazier 9/04/2014 James Johnston 9/04/2014 Johnny Munoz 9/04/2014

Michael Frazier Date James Johnston Date Johnny Munoz Date

Dir. Programs Aircraft Integration Engineer Certification Manager

Capstone-AML-0103

Capstone AML-0103 Page 2 of 7

REV F

REVISION PAGE

REVISION DESCRIPTION RELEASED BY DATE

IR Initial Release Randy Harper 02-15-13

A Added Cirrus models SR 20/22/22t/ and Cessna models 150/152 Randy Harper 08-05-13

B Added models in lines 24, 36 Randy Harper 08-16-13

C Added models in lines 25, 26, 27, 52, 53 Randy Harper 09-09-13

D Removed models having pressurized cabin and / or composite skins. Added installation restriction note, page 3 regarding random aircraft possibly certified for high altitude operation.

Randy Harper 03-10-14

E Removed additional models per FAA request (PA-46-310P, PA 42-1000)(Commander 680-695 series)(Beechcraft 60,100 series)(Cessna 412 series, 425).

Randy Harper 03-17-14

F Alphabetized Listing M. Frazier 09-04-14

Capstone-AML-0103


REV F

Note: Any aircraft certified for high altitude operation (pressurized cabin, FAR 23.841) are specifically not covered by this STC approved model listing.

ADS-B installation candidate aircraft certified for high altitude operation will require additional review/FAA approval via amendment of this AML

prior to STC installation.

Part 23, Class I Aircraft

Item Make/Model Designation

Type

Certificate

Date

Sheet

Certification

Basis

Installation

Instructions AFM Supplement

1

Beechcraft Models 35-33, A33, B33, C33, 36, A36, A36TC, B36TC,

E33, E33A, E33C, F33, F33A, F33C, G33, H35, J35, K35, M35, N35,

P35, S35, V35, V35A, V35B

3A15, Rev.

94

CAR Part 3

FAR Part 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

2 Beechcraft Models 35, 35R, A35, B35, C35, D35, E35, F35, G35 A-777, Rev.

58 CAR 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

3 Cessna Models 150A-M, A150L-M, 152, A152 3A19, Rev

48 CAR 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

4 Cessna Models 170, 170A, 170B A-799, Rev.

54 CAR 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

5 Cessna Models 172, 172A, 172B, 172C, 172D, 172E, 172F, 172H, 172I,

172K, 172L, 172M, 172N, 172P, 172Q, 172R, 172S

3A12, Rev.

83

CAR Part 3

FAR Part 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

6 Cessna Models 172RG, 175, 175A, 175B, 175C, P172D, R172E, R172F,

R172G, R172H, R172J, R172K

3A17, Rev.

46 CAR Part 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

7 Cessna Models 177, 177A, 177B A13CE, Rev.

28 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

8 Cessna Model 177RG A20CE, Rev.

22 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

9 Cessna Models 180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H,

180J, 180K 5A6, Rev. 67 CAR 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

Capstone-AML-0103


REV F


Type

Certificate

Date

Sheet

Certification

Basis

Installation


10

Cessna Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H,

182J, 182K, 182L, 182M 182N, 182P, 182Q, 182R, 182S, 182T, R182,

T182, TR182, T182T

3A13, Rev.

70 CAR Part 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

11 Cessna Models 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F 3A24, Rev.

39 CAR Part 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

12

Cessna Models 206, 206H, P206, P206A, P206B, P206C, P206D, P206E,

P206H, TP206A, TP206B, TP206C, TP206D, TP206E, TU206A,

TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, U206,

U206A, U206B, U206C, U206D, U206, U206E, U206F, U206G

A4CE, Rev.

48 CAR 3 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

13 Cessna Models 207, 207A, T207, T207A A16CE, Rev.

22 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

14

Cessna Models 210-5 (205), 210 -5A (205A), 210, 210A, 210B, 210C,

210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L, 210M, T210F,

T210G, T210H, T210J, T210K, T210L, T210M

3A21, Rev.

48

CAR Part 3

FAR Part 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

15 Commander Models 112, 112B, 112TC, 112TCA, 114, 114A, 114B,

114TC

A12SO, Rev.

22 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

16 De Havilland DHC-2 MKI, MKII, MKIII A-806, Rev

24

CAR 10, CAR

3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

17 Found Aircraft FBA-2C1, 2C2, 2C3, 2C4, 2C3T, 2C4T A7EA, Rev 8 CAR 3, FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

18 Helio Aircraft LLC H-250, H-296 1A8, Rev 34 FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

19 Lake Aircraft LA-4-200 1A13, Rev

27 CAR 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

20 Mooney Models M20, M20A, M20B, M20C, M20D, M20E, M20F,

M20G, M20J, M20K, M20L, M20M, M20R, M20S 2A3, Rev. 52 CAR Part 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

Capstone-AML-0103


REV F


Type

Certificate

Date

Sheet

Certification

Basis

Installation


21 Piper Models PA-12, PA-12S A-780, Rev.

13 CAR 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

22

Piper Models PA-18, PA-18S, PA-18 "105" (Special), PA-18S "105"

(Special), PA-18A, PA-18 "125" (Army L-21A), PA-18S "125", PA-

18AS "125", PA-18 "135" (Army L-21B), PA-18A "135", PA-18S "135",

PA-18AS "135", PA-18 "150", PA-18A "150", PA-18S "150", PA-18AS

"150", PA-19 (Army L-18C), PA-19S

1A2, Rev. 38 CAR Part 3 CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

23 Piper Models PA-24, PA-24-250, PA-24-260, PA-24-400 1A15, Rev.

34 CAR Part 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

24

Piper Models PA-28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-

161, PA-28-180, PA-28-181, PA-28-201T, PA-28-235, PA-28-236, PA-

28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28S-160, PA-

28S-180, PA-28RT-201, PA-28RT-201T

2A13, Rev.

50

CAR Part 3

FAR Part 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

25

Piper Models PA-32-260, PA-32-300, PA-32-301, PA-32-301T, PA-32R-

300, PA-32R-301, PA-32R-301T, PA-32RT-300, PA-32-300T, PA-32S-

300

A3SO, Rev.

32 CAR 3 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-AFMS-

0103 Rev B

Capstone-AML-0103


REV F

Part 23, Class II Aircraft


Type

Certificate

Date Sheet

Certification

Basis

Installation

Instructions

AFM

Supplement

1 B-N Group Limited BN-2, 2A, 2B, 2T A17EU, Rev 17 FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

2

Beechcraft Models 56TC, 58, 58A, 95, 95-55, 95-A55, 95-B55, 95-B55A,

95-B55B, 95-C55, 95-C55A, A56TC, B95, B95A, D55, D55A, D95A, E55,

E55A, E95

3A16, Rev. 87 CAR 3, FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

3 Beechcraft Models 58TCA A23CE, Rev.

15 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

4 Cessna Model 336 A2CE, Rev. 7 CAR 3 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

5 Cessna Model T303 A34CE, Rev. 6 FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

6

Cessna Models 310, 310A (USAF U-3A), 310B, 310C, 310D, 310E (USAF

U-3B), 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L,

310N, 310P, T310P, 310Q, T310Q, 310R, T310R

3A10, Rev. 62 CAR 3,FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

7 Cessna Models 320, 320-1, 320A, 320B, 320C, 320D 320E, 320F, 335 3A25, Rev. 25 CAR 3, FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

8 Cessna Models 337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H,

M337B, T337B, T337C, T337D, T337E, T337F, T337H, T337H-SP A6CE, Rev. 40 CAR 3, FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

9 Piper Models PA-30, PA-39, PA-40 A1EA, Rev. 18 CAR 3, FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

10 Piper Models PA-34-200, PA-34-200T, PA-34-220T A7SO, Rev. 18 FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

11 Piper Models PA-44-180, PA-44-180T A19SO, Rev.

12 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

Capstone-AML-0103


REV F

Part 23, Class III Aircraft (Unpressurized Versions Only)


Type

Certificate

Date Sheet

Certification

Basis

Installation

Instructions

AFM

Supplement

1 Beechcraft Models 58TC A23CE, Rev.

15 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

2 Beechcraft Models 99, 99A, 99A (FACH), C99, A99, (U-21F), A99A, B99 A14CE, Rev.

37 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

3 Cessna Models 208, 208A, 208B A37CE, Rev.

18 FAR 23

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

4 Cessna Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A A7CE, Rev. 48 CAR 3 FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

5 Commander Models 500, 500-A, 500-B, 500-U, 520, 560 560-A, 560-E,

500-S 6A1, Rev. 46 CAR 3

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

6 Commander Models 560-F, 680, 680E, 685, 690, 690A, 690B, 690C, 690D 2A4, Rev. 47 CAR 3 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

7 De Havilland DHC-3 A-815, Rev 6 CAR 10, CAR

3

CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

8 Piper Models PA-31, PA-31-300, PA-31-325, PA31-350 A20SO, Rev.12 CAR 3, FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

9 Piper Models, PA-31T, PA-31T1, PA-31T2, PA-31T3, A8EA, Rev. 24 CAR 3, FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

10 Reims-Cessna F406, Caravan II A54EU FAR 23 CAPSTONE-II-

0103 Rev E

CAPSTONE-

AFMS-0103 Rev B

DESCRIPTION

REVISIONS

DATE NAME

6 7 854

AA

321

DD

CC

FF

1 2 3 4 5 6 7 8 CAD GENERATED DRAWING,DO NOT MANUALLY UPDATE

FF

CC

BB

AA

REV

SHEET OFDO NOT SCALE DWG

PROJECTION

UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES,

TOLERANCE ON:

DRAWING INTERPRETATION

.XXX ± .010

.XX ± .03

.X ± .1

ANGULAR ± 2°

PER MIL-STD-100INTERPRET DIMENSIONS ANDTOLERANCES PERANSI Y14.5M-1982

THE INFORMATION, TECHNICAL DATA, AND DESIGNS, DISCLOSED HEREIN ARE THE

EXCLUSIVE PROPERTY OF RANDY HARPER AEROSPACE, PLLC, OR CONTAIN PROPRIETARY RIGHTS OF RHA CUSTOMERS AND SHALL NOT

BE USED OR DISCLOSED TO ANOTHER WITHOUT THE WRITTEN CONSENT OF RANDY

HARPER AEROSPACE PLLC. THE RECIPIENT OF THE DATA, BY AGGREES TO HOLD IN

CONFIDENCE THE TECHNICAL DATA AND DESIGNS CONTAINED WITHIN. THIS DOES NOT

APPLY TO PERSONS ALREADY HAVING PROPRIETARY RIGHTS TO COVERED

INFORMATION, TECHNICAL DATA, OR DESIGNS, TO THE EXTENT THAT SUCH RIGHTS EXIST.

FREEFLIGHT SYSTEMS INC.TITLE:

DWG NOAPPROVED BY:

CHECKED BY:

DRAWN BY:

IR INITIAL RELEASE 12-10-12 R. HARPER

LISTED ITEMS INCLUDED IN ITEM 3 INSTALLATION KIT.11

NOTES:

REFERS TO SIMILAR SYMBOL WITH SAME LETTER IN THIS DRAWING.

NOTE- ONLY GROUNDS OF THE SAME LETTER CODE SHALL OCCUPY THE SAME GROUND LUG OR TERMINAL BLOCK.THE FOLLOWING NOTES APPLY FOR ALL GROUNDS:

AC GROUND

DENOTES EXISTING AIRCRAFT WIRING OR COMPONENT.DENOTES AN EXISTING ASSEMBLY.DENOTES A NEW WIRE, ASSEMBLY OR COMPONENT.

a) CONN. TERM.TO GROUND TERM. POINT SHALL BE AS SHORT AS POSSIBLE.

FOR THE FOLLOWING GROUND TYPES:

ALL UNIDENTIFIED WIRES SHALL BE 22 GUAGE P/N M22759/34-22-9 AND SHALL NOT TO EXCEED 6" IN LENGTH

PROGRAM/MODE CONTROL DISCRETE

a) SHIELD SHALL BE GROUNDED AT ALL BREAK POINTS.

CHASSIS OR SHIELD GROUND

a) SHIELD CONTINUITY SHALL BE MAINTAINED THROUGH ALL BREAK POINTS.

a) WIRE EXPOSED BETWEEN SHIELD TERM. AND CONN. SHALL NOT EXCEED 3" LENGTH.


b) ALL SHIELD GROUND WIRES SHALL NOT EXCEED 6" LENGTH.


E

FOR ALL SHIELDED WIRE:

UNLESS OTHERWISE NOTED.

D

DC GROUNDA

7.

B

4.

5.

6.

2.

3.

1.

F SPECIAL SHIELD GROUNDS.

SIGNAL RETURNC

12

LISTED ITEMS INCLUDED IN ITEM 12 INSTALLATION KIT. KIT CONSISTS OF COMPONENTS FROM TRIG INSTALLATION KIT 00859-00.13

9.

DURING INSTALLATION THIS DRAWING SHALL BE COORDINATED WITH WIRE ROUTING DRAWING NO. CS-0103-RT WHICH INCLUDES ADDITIONAL DETAILS FOR HIRF, LIGHTNING SYSTEM SEPARATION.

REFER TO SHEET 2 FOR BILL OF MATERIALS AND ADDITIONAL NOTES

CONNECTION OF NEW CIRCUIT BREAKERS TO POWER BUS SHALL BE MADE MAINTAINING AWG TO MATCH EXISTING BUS FEEDER.

15

17

16

18

14

AFTER INSTALLATION CIRCUIT BREAKER PANEL SHALL BE ENGRAVED OR PLACARDED TO IDENTIFY SYSTEM CIRCUIT BREAKER AS INDICATED ON THIS DRAWING.

FABRICATE A COAX CABLE TO LENGTH (MAX 10'). CUT ONE END OF THE COAXIAL CABLE ON AN ANGLE AND INSPECT TO ENSURE THAT THE OUTER SHIELD AND CENTER CONDUCTOR ARE NOT SHORTED. INSTALL ITEM 61 DUST CAP & ITEM 48 HEAT SHRINK. ROUTE CABLE FROM ANTENNA TO FTM-190C AND INSTALL SMA CONNECTOR.

30

8

31

VERIFY EXISTING DATA BUS CONTINUITY WHEN SPLICING INTO EXISTING WIRING HARNESS AS SHOWN.

23

INSTALLATIONS HAVING A TRANSPONDER WITH ALT DATA OUTPUT TERMINATE WIRING AS SHOWN.THE TRANSPONDER MONITOR IS NOT REQUIRED IN EXISTING TRANSPONDER INSTALLATIONS WITH DATA BUS OUTPUTS.24

E

D

25

COAXIAL CABLES SHALL BE MARKED WITH SLEEVES PER WIRE ROUTING DRAWING CS-0103-RT REFERENCES.

LISTED ITEMS INCLUDED IN ITEM 7 INSTALLATION KIT.

LOSS OVER ENTIRE COAX LENGTH SHALL NOT EXCEED 10 dB.

26


19

27


INSTALL STOWED END OF COAX WITHIN A MAX DISTANCE OF 12" (1 FOOT) FROM THE MOUNTING PLATE OF THE TRANSPONDER ANTENNA.

28


ALL INSTALLED ANTENNAS ARE TO HAVE SURFACE TO SURFACE ELECTRICAL BONDING OVER ENTIRE BASE OF ANTENNA. SURFACE SHALL BE CLEANED OF ALL PAINT AND TREATED WITH CONDUCTIVE ALODINE.




AFTER INSTALLATION CONFIGURATION AND SETUP SHOULD BE ACCOMPLISHED PER CAPSTONE-II-0103. ICAO 24 BIT ADDRESS SHOULD BE OBTAINED PRIOR TO CONFIGURATION START.

20

21 LISTED ITEMS INCLUDED IN ITEM 63 INSTALLATION KIT.

E

BB

D1 36

WIRING DIAGRAM FDL-978-XVR

CS-0103-WD

WITH OPTIONAL INSTALLATIONS, OMIT COMPONENTS AND ASSOCIATED WIRING WHEN NOT INSTALLED.32

33 CONNECT FDL-978-XVR J1 -32 REMOTE ON TO AIRCRAFT GROUND WHEN TC978 CONTROL IS NOT INSTALLED.

34

UNLESS OTHERWISE NOTED, ALL ELECTRICAL CABLE SHALL BE PER MIL-DTL (NEMA WC) 27500 P/N M27500-XXSDXT23 FOR SHIELDED JACKETED CABLE AND P/N M27500-SDXU23 FOR UNSHIELDED JACKETED CABLE WHERE "XX" DENOTES THE WIRE GAUGE AS DETERMINED BY THE LAST 1 OR 2 DIGITS OF EACH WIRE NUMBER AND "X" DENOTES THE NUMBER OF CONDUCTORS WITHIN THE CABLE AS SHOWN ON THE WIRING DIAGRAM. MULTIPLE CONDUCTOR WIRE COLOR REFERENCE: WHITE (W), BLUE (B), ORANGE (O). COLOR INDICATED IN WIRE NUMBER MAY VARY DEPENDING UPON WIRE MANUFACTURER.

BEFORE BEGINNING WIRE ROUTING, LOCATE ALL WIRES USED FOR FUEL QUANTITY INDICATION. WHEN ROUTING BUNDLES AND COAX, MAINTAIN A MINIMUM SEPARATION OF 2 INCHES FROM THE FUEL QUANTITY WIRES. INSTALL WIRING FOLLOWING EXISTING WIRE BUNDLES WHERE PRACTICAL. FOR ADDITIONAL ROUTING, BONDING AND GROUNDING DETAILS REFER TO: AC 43.13-1B CHAPTER 11, SECTIONS 9, 10, 11 & 15; AC 43.13-2B PARAGRAPH 207(d); S.A.E. AS50881 D WIRING AEROSPACE VEHICLES AND WIRE ROUTING DRAWING AK-WR-001.

UNLESS OTHERWISE NOTED, ALL SINGLE CONDUCTOR STRANDED WIRE SHALL BE PER MIL-W-22759 P/N M22759/34-XX-9 WHERE "XX" DENOTES THE WIRE GAUGE AS DETERMINED BY THE LAST 1 OR 2 DIGITS OF EACH WIRE NUMBER ON THE WIRING DIAGRAM.

22

REPLACE EXISTING GPS ANTENNA WITH P/N SHOWN. REFER TO ANTENNA INSTL DRAWING NO. AK-ANT-001 FOR MECHANICAL INSTALLATION DETAILS.

35AN INSTALLATION KIT IS INCLUDED WITH THE ALTITUDE ENCODER. A DA-15S D-SUB CONNECTOR, A 15 PIN CONNECTOR BACKSHELL, TUBING, ACCESSORIES FOR STATIC SYSTEM PLUMBING AND AN OWNER/INSTALLATION MANUAL ARE INCLUDED.

REFER TO EXISTING AIRCRAFT WEIGHT ON WHEELS SYSTEM. TERMINATE NEW WIRING SHOWN TO PROVIDE LOGIC FOR AIRCRAFT ON THE GROUND TO FDL-978-XVR.

10

LISTED ITEMS INCLUDED IN ITEM 24 & 29 INSTALLATION KITS.

DURING INSTALLATION THIS DRAWING SHALL BE COORDINATED WITH EQUIPMENT INSTL DRAWING NO. CS-0103-SEN, ANTENNA INSTL DRAWING NO. CS-0103-ANT, AND INSTALLATION INSTRUCTIONS REPORT NO. CAPSTONE-II-0103.

J JOHNSTON 07/23/2014

B POONAWALLA 07/25/2014

M FRAZIER 07/25/2014

A

SEPERATE RCEP FROM STANDARD INSTALL, ADDED CHELTON WIRING, CLARIFIY QCR PINS

08-12-13 R. HARPER

C:/Users/James/Pictures/FreeFlight/FFSlogoFINAL.jpg

B ADD PORT 3 RS232 MAINTENANCE INTERFACE 09-18-14 J. JOHNSTON

ADD DEPICTION OF GDL 90 J1 ON SHEET 3

29

ADD CONNECTIONS FOR ASPEN PFD AND MFD ON PAGE 3C 11-20-14 J. JOHNSTON

D 06-16-15 J. JOHNSTON

D

A. THIS DRAWING IS STRUCTURED AS FOLLOWS:SH3-13 SHOW THE SPECIFIC CONNECTIONS FOR FDL-978-RX AND FDL-978-XVR PRODUCTS.SH14-25 SHOW THE SPECIFIC CONNECTIONS FOR USING AN FDL-978 SERIES PRODUCT IN A QUICK CHANGE RACK ASSEMBLY.SH26-31 SHOW THE SPECIFIC CONNECTIONS FOR FDL-978-TXL AND FDL-978-XVRL PRODUCTS.EACH SHEET CONTAINS A NOTATION FOR WHICH PRODUCT SERIES IS DESCRIBED ON THAT SHEET.

D

IDENTIFIES CHANGE FROM PREVIOUS DRAWING REVISION.

SYMBOL DEFINITION:

D

ADD CONNECTIONS FOR GNS 430/530 GPS SOURCE INCLUDING SINGLE-ENDED PPS CONNECTION DIAGRAM AND RESISTOR INFORMATION. ADDED CONNECTION DIAGRAMS FOR FDL-978 LITE VERSIONS. REFORMATTED DRAWING FOR READABILITY. CORRECTED TRANSPONDER PINOUTS. ADDED ADDITIONAL TRANSPONDER RS232 PORT CONNECTION OPTIONS. CHANGED POWER WIRE TO 22AWG. CLARIFIED FDL-978 PART TITLES. CHANGED CIRCUIT BREAKER VALUE ON FDL-978 TO MATCH INSTALL MANUAL. CHANGED ANNUNCIATOR LIGHT FROM GREEN TO AMBER. ADDED INSTALL KIT NOTES TO ANTENNA CONNECTION DIAGRAMS. ADDED MISSING WIRE NUMBERS WHERE NEEDED. CORRECTED CONNECTOR DESCRIPTIONS ON QCR DIAGRAMS.

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11

PARTS AND QUANTITIES REQUIRED VARY WITH INSTALLATIONS SHOWN

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12

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21

PARTS AND QUANTITIES REQUIRED VARY WITH INSTALLATIONS SHOWN

14

15

16

17

18

19

36INSTALLED UNDER SEPERATE APPROVAL.

19

FREEFLIGHT87002-10PERSONALITY MODULE INST'L KIT17-1

REF QTY PART NUMBERDESCRIPTION VENDOR/MANUFINST INST-03 -01

FREEFLIGHT85945-00-APERSONALITY MODULE18-1FREEFLIGHT86967CRIMP PIN 24-28 AWG49-4FREEFLIGHT87006DOUBLE-SIDED ADHESIVE TAPE110-1TRIG AVIONICS00808-00-04TC978 CONTROLLER111A/R1FREEFLIGHT86964TC978 INST'L KIT112A/R1

FREEFLIGHT87098-10-XXXXFDL-978 W/O INTERNAL GPS12-1FREEFLIGHT85935-00FDL-978-XVR INST'L KIT13-1FREEFLIGHT85942DB-44 BACKSHELL14-1FREEFLIGHT86945DB-44 MALE CRIMP CONNECTOR15-1FREEFLIGHT86967CRIMP PIN 24-28 AWG506-50

FREEFLIGHT87098-00-XXXXFDL-97811-1

FREEFLIGHT87093DB-15 CRIMP CONNECTOR154-A/RFREEFLIGHT87231-00WI-FI INST'L KIT153-A/RFREEFLIGHT86943-00WI-FI HOTSPOT TRANSMITTER152-A/RQPLM81824/1-2SPLICE, IN-LINE, CRIMP (BLU)551-A/RQPLM81824/1-1SPLICE, IN-LINE, CRIMP (RED)2150A/RA/RFREEFLIGHT0123-0012-00RG-142 CABLE10'49-A/R

TRIG AVIONICS00732-00HOSE CONN 3/16" NYLON TEE118A/RA/RTRIG AVIONICS00731-00HOSE EDPM RUBBER 5mm ID - 8mm OD117A/RA/RTRIG AVIONICS00678-00TC978 MTG ADPT BRKT CIRCULAR116A/RA/RTRIG AVIONICS00730-00CRIMP SOCKET 20-24 AWG915A/R9TRIG AVIONICS00725-00DB-9 BACKSHELL114A/R1TRIG AVIONICS00727-00DB-9F CONNECTOR, RECEPTACLE113A/R1

FREEFLIGHT87003-00BLADE ANTENNA INST'L KIT224A/R2TRIG AVIONICS00737-00SCREW, CSK, BLK, 4-40 UNC x 0.625"123A/RA/RTRIG AVIONICS00736-00SCREW, CSK. BLK. 4-40 UNC x 1.5"422A/RA/RTRIG AVIONICS00735-00HOSE CLAMP APPLIC DIA 9.5 - 10.3mm221A/RA/RTRIG AVIONICS00734-00HOSE CLAMP APPLIC DIA 8.5 - 9mm620A/RA/RTRIG AVIONICS00733-00HOSE ADPT STRGT NYLON 3/16" - 1/4"219A/RA/R

FREEFLIGHT85937BALL & STICK UAT ANTENNA130A/RA/RFREEFLIGHT87004-00BALL & STICK ANTENNA INST'L KIT229A/RA/RFREEFLIGHT0123-0012-00RG-142 COAX CABLE25'28A/RA/RFREEFLIGHT0129-0017-00TNC CRIMP CONNECTOR, MALE RG142127A/RA/RFREEFLIGHT86966BNC RG142 MALE CRIMP CONNECTOR126A/RA/RFREEFLIGHT87005BLADE TYPE UAT ANTENNA125A/RA/R

FREEFLIGHT0129-0017-00TNC CRIMP CONNECTOR, MALE RG142236A/RA/RFREEFLIGHT81194GPS WAAS ANTENNA DO-228, TSO-C144135A/RA/RFREEFLIGHT87360-10TSO-C144 GPS ANTENNA INST'L KIT134A/RA/RFREEFLIGHT0123-0012-00RG-142 COAX CABLE25'33A/RA/RFREEFLIGHT0129-0017-00TNC CRIMP CONNECTOR, MALE RG142132A/RA/RFREEFLIGHT86966BNC RG142 MALE CRIMP CONNECTOR131A/RA/R

FREEFLIGHT86930-00-101AFTM-190C TRANSPONDER MONITOR142-A/RFREEFLIGHT0123-0012-00RG-142 COAX CABLE25'41A/RA/RFREEFLIGHT0129-0017-00TNC CRIMP CONNECTOR, MALE RG142240A/RA/RFREEFLIGHT86735GPS ANTENNA DO-301, TSO-C144139A/RA/RFREEFLIGHT87360-00TSO-C190 GPS ANTENNA INST'L KIT138A/RA/RFREEFLIGHT0123-0012-00RG-142 COAX CABLE25'37A/RA/R

FREEFLIGHT9-3154-050-00HEAT SHRINK148-A/RFREEFLIGHT87027SMA CRIMP MALE RG-142147-A/RFREEFLIGHT84194CRIMP PIN 24-28 AWG1746-A/RFREEFLIGHT87094DB-15 BACKSHELL145-A/RFREEFLIGHT87093DB-15 FEMALE CRIMP CONNECTOR144-A/RFREEFLIGHT87113-00FTM-190C INSTALLATION KIT143-A/R

FREEFLIGHT84194CRIMP PIN 15-DSUB1556-A/RAMPHENOLL717SDC37PGDL-REV5-2 P1 CONNECTOR157-13M8P15-N001GDL-REV 5-2 P2 CONNECTOR158-1TED9-30-10TRAY MOUNT RF ANTENNA CONNECT359-3QPLMS3320-2CIRCUIT BREAKER 2 AMP260-A/R

FREEFLIGHT87229DB-15 BACKSHELL155-A/R

REF QTY PART NUMBERDESCRIPTION VENDOR/MANUFINST INST-03 -01

FREEFLIGHT84100-03-0304 OR 84100-03-0306GPS/WAAS 1201 SENSOR162-A/RFREEFLIGHT84142-01INSTALLATION KIT, GPS/WAAS 1201163-A/RFREEFLIGHT84140CONN, RECEPTACLE, 25 PIN D-SUB164-A/RFREEFLIGHT84141SOCKET, CRIMP STYLE, FEMALE2565-A/RFREEFLIGHT84198 (ALT. 84150)BACKSHELL ASSY, 25-POS, 90 DEG EXT166-A/R

RAYCHEMES-CAP-NO.1-C1--0-30MMES CAP, ENVIRONMENTAL SHRINKABLE161A/RA/R

RAYCHEMCWT-5-W122-5SHIELD TERMINATION, SOLDER SLEEVE1669-A/RQPLMS3320-1CIRCUIT BREAKER 1 AMP170-A/RTRANS-CAL INCSSD120-(XX)N(X)-RS232ALTITUDE ENCODING UNIT171-A/REATON58210A2B0C1F4L5N1(A),P12B,12 ADS BADS B ANNUNCIATOR LIGHT/SWITCH172-A/R

QPLMS25036-149RING TERMINAL #8 22-18 AWG1967-A/R

FREEFLIGHT85937ANTENNA XPNDR UAT TX/RX FDL-978174-A/RFREEFLIGHT87027CONNECTOR SMA STRGT RG142 CRIMP175A/RA/RFREEFLIGHT85937CONNECTOR BNC RG142 CRIMP176A/RA/RFREEFLIGHT87218-00QUICK CHANGE RACK ASSEMBLY177A/RA/R

PCD-TYCOTJSE20701DIODE SPLICE SINGLE173A/RA/R

POSITRONICSD9000JVL010 PIN HYBRID BACKSHELL1791-POSITRONICSCBM11W1F20HT0-010 PIN HYBRID CONNECOTR, RECEPTACLE1781-

QPL1N4001DIODE AXIAL LEAD268A/RA/R

FREEFLIGHT87215-00WIRING HARNESS1801-

FREEFLIGHT SYSTEMS INC.

37FOR -01 INSTALLATIONS WHICH DO NOT REQUIRE A TC978 CONTROLLER INSTALL ITEM 82 GROUNDING CONNECTOR AND WIRING AS SHOWN.

38FOR -01 INSTALLATIONS WHICH REQUIRE THE CAGE/FRAME WITH HARNESS INSTALL THE PM INSIDE THE BACKSHELL FOR J1 OUTSIDE THE CAGE/FRAME ASSEMBLY WIRING.

FREEFLIGHT87419-00REMOTE-ON CONNECTOR181A/RA/R

WITH SHIELDED WIRE, EXCEPT WHEN THE SHIELD IS ACTING AS THE SERIAL COMMON GROUND, ONLY GROUND ONE END. GROUNDING BOTH ENDS MAY INDUCE NOISE.39

40 FOR -01 INSTALLATIONS, Wi-Fi MODULE PROVISIONS ARE INCLUDED IN THE QCR. NO ADDITIONAL WIRING IS NECESSARY.

TC-978 MUST BE DISCONNECTED WHEN USING PORT 3 RS232 CONNECTIONS.41

FREEFLIGHT87681GENDER CHANGER KIT1821-

DOUBLE-SHIELDED CABLE IS REQUIRED FOR THE ASPEN EFD500/EFD1000 DISPLAY. SINGLE-SHIELDED CABLE SHOULD BE USED OTHERWISE.42

43 FOR ASPEN EFD500/EFD1000 INSTALLATIONS, THE PFD IS REQUIRED FOR ADS-B OUT INSTALLATIONS.

44 DISCONNECT TC978 WHEN CONNECTING TO THE RS232 FOR PORT 3 MAINTENANCE INTERFACE

45 RS232 INTERFACE FOR PORT 5 IS AVAILABLE ON PART NUMBERS 87098-xx-xxxx BUT NOT ON 87098-00 AND 87098-10.

FREEFLIGHT84192DB9 FEMALE183-A/RFREEFLIGHT83145CRIMP PIN BARREL384-A/R

46 ANY RS232 PORT, 1-5, FROM THE GNS 400/500 UNIT MAY BE USED FOR GPS DATA OUTPUT IN THE ADS-B OUT+ FORMAT.

47 THE SGND WIRE MUST BE TIED TO THE SAME GROUND CONNECTION AS THE GNS 400W/500W.

RS232 SERIAL PORT 1 OR 2 MAY BE USED.49

50

TTIRESISTOR, 160 OHMS, 5%, .25WRESISTOR, 160 OHMS, 5%, .25W385-A/RTTIRESISTOR, 430 OHMS, 5%, .25WRESISTOR, 430 OHMS, 5%, .25W386-A/RQPLMS3320-1/2CIRCUIT BREAKER 0.5 AMP187-A/R

PERSONALITY MODULE SHOULD BE MOUNTED INSIDE THE 15-PIN CONNECTOR BACKSHELL.

D

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51 SEE MANUFACTURER INSTALLATION MANUAL FOR CORRECT PIN NUMBERS.

48 RESERVED.

52 ONLY ONE MAINTENANCE PORT IS REQUIRED.

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FDL-978-XVR AND -RX POWER, PM, AND AIR/GNDSWITCH INSTALLATIONS ASPEN EFD CONNECTION

2

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50

5160

2610

67

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3

4 5 6

7

FREEFLIGHT SYSTEMS INC. D

38

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D6739

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REFER TO THE MANUFACTURERS DOCUMENTATION TO VERIFY THE INTEGRATION DATA AND FOR CHECKOUT PROCEDURES. THIS DRAWING AS IT PERTAINS TO THE NON-FREEFLIGHT EQUIPMENT IS FOR REFERENCE ONLY. STC SA02426AK DOES NOT INCLUDE INSTALLATION APPROVAL OF THE NON-FREEFLIGHT EQUIPMENT.

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FDL-978-XVR AND -RX PORT 3 ANDPORT 5 RS232 MAINTENANCE PORT INTERFACE. FREEFLIGHT SYSTEMS INC. D

39A

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FDL-978-XVRANNUNCIATOR INSTALLATIONS

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81 2 3

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FDL-978-XVR L-BAND SUPPRESSION INSTALLATIONS

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FDL-978-XVR AND -RX INTERNAL GPS ANTENNA INSTALLATIONS

GPS ANTENNA

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36 40

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OPTIONAL EXTERNAL 1201 GPS/WAAS GPS ANTENNA INSTALLATIONS

OPTIONAL 32

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26 3125

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20 25

32

2833 2833BOT UAT ANTENNA

26 3125

23

3031 26

FDL-978-XVR AND -RX TOP UAT ANTENNA INSTALLATIONS

FDL-978-XVR AND -RX BOT UAT ANTENNA INSTALLATIONS

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FREEFLIGHT SYSTEMS INC.54321

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FDL-978-XVR AND -RX OPTIONAL ALTITUDE ENCODER INSTALLATIONS

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FDL-978-XVR AND -RX TRANSPONDER CONTROL OPTIONAL INSTALLATIONS

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FDL-978-XVR AND -RX W/O INTERNAL GPS

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-01 INSTALLATION

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THE FOLLOWING PAGES DESCRIBE THE -01 INSTALLATION USING THE QCR (QUICK CHANGE RACK)

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QCR ANNUNCIATOR SWITCH; L-BAND SUPPRESSION INSTALLATIONS

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GPS ANTENNA59

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QCR GPS ANTENNA INSTALLATIONS

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1201 GPS/WAAS GPS ANTENNA INSTALLATIONS

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-01 INSTALLATION

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DFREEFLIGHT SYSTEMS INC.

TOP UAT ANTENNA

592833

QCR TOP UAT ANTENNA INSTALLATIONS

QCR BOTTOM UAT ANTENNA INSTALLATIONS

-01 INSTALLATION

592833

BOTTOM UAT ANTENNA

-01 INSTALLATION

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-01 INSTALLATIOND

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FREEFLIGHT SYSTEMS INC.QCR SERIAL MFD INSTALLATIONS

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CHELTON ONLY

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-01 INSTALLATION

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3258

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8 69

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QCR ARINC 429 TRAFFIC INSTALLATIONS

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FDL-978-XVRL ANNUNCIATOR INSTALLATIONS.

ADS B

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FREEFLIGHT SYSTEMS INC.FDL-978-XVRL AND -TXL CONTROL CONNECTION FROM TRANSPONDER.

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FDL-978-XVRL AND -TXL GPS ANTENNA INSTALLATIONS

GPS ANTENNA

35

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1716 1716 1716

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FREEFLIGHTSYSTEMS

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BC

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FREEFLIGHTSYSTEMS

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3

NEW BUNDLE OR TUBE

NEW BUNDLE

CAT TRACK

MS21919WDG-( )CABLE CLAMP

GROMMET

ANGLE BRACKET WITHTWO POINT FASTENING

ANGLE BRACKET WITHTWO POINT FASTENING

CLEARANCE .38" MINIMUM


WIRES LESS THAN .38"FROM HOLE EDGE

EXISTING BUNDLES

NEW WIRE BUNDLE

NEW WIRE BUNDLESLEEVE BUNDLE AS NECESSARYTO PREVENT CHAFING USING:

PN: XPF-( XXX )( XXX ) = BUNDLE DIAMETER

MANUFACTURER: ICO-RALLY

MS35207, AN525, MS27039,OR NAS603 SCREW

MS21919EH5, MS21919WDG-( )CABLE CLAMP

AN365, NAS679, ORMS21042 NUT NAS1149 OR AN960 WASHER

NEW WIRE BUNDLE EXISTING BUNDLES

NAS1149 OR AN960 WASHERAN365, NAS679, ORMS21042 NUT

MS21919EH5, MS21919WDG-( )CABLE CLAMPS

MS35207, AN525, MS27039,OR NAS603 SCREW

EXISTING BUNDLE OR TUBE

EXISTING BUNDLE

MS35207, AN525, MS27039,OR NAS603 SCREW MS21919EH5, MS21919WDG-( )

CABLE CLAMPS

AN365, NAS679, ORMS21042 NUT NAS1149 OR AN960 WASHER

NAS43 SPACER

STEP A:WIRING MUST BE ROUTED ABOVE COMBUSTIBLEFLUID OR OXYGEN LINES AND EQUIPMENT WITH AMINIMUM OF 6" SEPARATION BETWEEN.

STEP B:WHEN "STEP A" IS NOT PRACTICAL, WIRING MUSTBE ROUTED SO THAT IT DOES NOT RUN PARALLELTO COMBUSTIBLE FLUID OR OXYGEN LINES.

STEP C:A MINIMUM OF 2" MUST BE MAINTAINED BETWEENWIRING AND COMBUSTIBLE FLUID OR OXYGENLINES AND EQUIPMENT EXCEPT WHEN THEWIRING IS POSITIVELY CLAMPED TO MAINTAIN AMINIMUM OF .50 IN SEPARATION WHEN WIRINGMUST BE CONNECTED DIRECTLY TOFLUID-CARRYING EQUIPMENT.

STEP D:CLAMPS INSTALLED ON FLUID LINESSHOULD NOT BE USED AS A MEANSTO SUPPORT WIRE BUNDLES.

STEP E:ADDITIONAL CLAMPS SHOULD BEINSTALLED TO SUPPORT THE WIREBUNDLE AND THESE CLAMPSFASTENED TO THE SAME STRUCTUREUSED TO SUPPORT THE FLUID LINESTO PREVENT RELATIVE MOTION.


TY WRAP HOLDER - P/N SS7036-600TY WRAP - P/N TY253MXPROTECTIVE TAPE P/N 608036-1

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FREEFLIGHTSYSTEMS

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Capstone-ICA-0103

Page 1 of 21 Rev C

FreeFlight Systems

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

For

APPROVED MODEL LIST

For ADS-B SYSTEM

Installed in Approved Model List Aircraft

Report No. Capstone-ICA-0103

Prepared by: J. Johnston

Approved by: M. Frazier

Capstone-ICA-0103

Rev. C 2 of 21

Table of Contents:

1 Record of Revisions ................................................................................................ 4 2 List of Effective Pages ............................................................................................ 4 3 Abbreviations .......................................................................................................... 5 4 Introduction ............................................................................................................. 5

4.1 Purpose ................................................................................................................ 6 4.2 Effectivity ........................................................................................................... 6 4.3 Part Number Equivalency ................................................................................... 7 4.4 Reference Documents ......................................................................................... 7 4.5 Applicable FAR .................................................................................................. 7

5 GENERAL .............................................................................................................. 7 5.1 GENERAL WIRING INSTRUCTIONS ............................................................ 7 5.2 Wire Separation .................................................................................................. 7

5.3 Wire Routing ....................................................................................................... 7 5.4 Securing Wire Bundles ....................................................................................... 8 5.5 Wire Termination ................................................................................................ 8

6 System Description ................................................................................................. 8 6.1 1201 GPS/WAAS (When installed).................................................................. 11 6.2 SYSTEM COMPONENTS ............................................................................... 11

7 Control and Operation Information ...................................................................... 12 7.1 Controls (Existing, Added) ............................................................................... 12 7.2 Displays............................................................................................................. 12

8 SERVICING INFORMATION ............................................................................ 13 8.1 TRANSPONDER ............................................................................................. 13 8.2 1201 GPS/WAAS (When installed).................................................................. 13 8.3 FDL-978 Series UAT ADS-B system............................................................... 13

8.4 FTM-190C Transponder Monitor (When installed) ......................................... 13 8.5 TC-978 ADS-B Controller (When installed) .................................................... 13 8.6 WI-FI (When installed) ..................................................................................... 13 8.7 FDL978 Series UAT ADS-B SYSTEM ADS-B, 1201 GPS/WAAS SYSTEM

SOFTWARE ................................................................................................................. 13 9 MAINTENANCE INSTRUCTIONS ................................................................... 13

9.1 General .............................................................................................................. 13 9.2 Servicing ........................................................................................................... 14

10 Troubleshooting Information ................................................................................ 14 10.1 Internal and External GPS ................................................................................ 14 10.2 FDL-978 TROUBLESHOOTING PROCEDURE ........................................... 15

11 Removal and Replacement Information ............................................................... 16 12 Wiring Diagrams (Interface Diagram) .................................................................. 18

13 Special Inspection Requirements .......................................................................... 18 14 Application of Protective Treatments ................................................................... 18 15 Data for Structural Fasteners ................................................................................ 18 16 List of Special Tools ............................................................................................. 18 17 Commuter Category Aircraft ................................................................................ 18

18 Recommended Overhaul Periods .......................................................................... 18 19 Weight and Balance .............................................................................................. 19

Capstone-ICA-0103

Rev. C 3 of 21

20 Airworthiness Limitations .................................................................................... 19 21 Structural Inspections: .......................................................................................... 19 22 Annual Inspections: .............................................................................................. 19 23 Revisions ............................................................................................................... 19 24 Installed Equipment List ....................................................................................... 20 25 Appendix A (Drawings) Note to the Installer ....................................................... 21

Capstone-ICA-0103

Rev. C 4 of 21

1 Record of Revisions

REV DATE BY DESCRIPTION

- 02-10-14 RDH Initial Release

A 09-04-14 M. Frazier

TSO Part Number Update

FDL-978-RX Inclusion

Equivalent Part Number Reference

B 02-13-15 J. Johnston Added the Aspen EFD 1000 and 500 to the list of

displays in Table 1. No other changes

C 06-08-15 J. Johnston

Corrected note reference from rotorcraft to airplane.

Added Maintenance and design changes to

interfacing components per AC 20-165A. Remove

Revision reference to Qualified Parts list in section

4.4. Improved System Description. Changed

references of FDL-978-XVR to FDL-978. Removed

Table1 Approved Configurations (redundant to the

Installation Instructions). Added references to the

Lite versions. Corrected the Troubleshooting

Information Section. Change a note in Section 11

regarding re-installation. Removed references to

Installation documentation and replaced with actual

installation data in Appendix A.

2 List of Effective Pages

For incremental changes each revised page will have (-X) following current revision (E.g. A-1, A-2) until

entire document is revised to the next letter level. Current page revision will be reflected in the table

below at each change. In addition:

Changes made to a line will be indicated by a vertical bar in the left margin next to the line.

Changes made to a paragraph should be indicated by a vertical bar in the left margin next to the

paragraph letter or number.

Changes made to a complete page should be indicated by a vertical bar to the right of the page

number

TITLE/SECTION

Revised

PAGES REV NO.

Manual-All All -

Manual-All All A

Approved Configurations Table 10 B

Manual-All All C

ATTACHMENTS See Appendix A

Capstone-ICA-0103

Rev. C 5 of 21

3 Abbreviations

a. FAA Federal Aviation Administration

b. FAR Federal Aviation Regulation

c. ICA Instructions for Continued Airworthiness

d. ADS-B Automatic Dependent Surveillance-Broadcast

e. LRU Line Replaceable Unit

f. TCAS Traffic Collision Avoidance System

g. GPS/WAAS Global Position Sensor/Wide Area Augmentation System

h. SSR Secondary Surveillance Radar

i. FFS FreeFlight Systems

j. IETP Interactive Electronic Technical Publication

4 Introduction

WARNING: Means a maintenance procedure, practice, condition, etc. that could result in personal injury or loss of life.

CAUTION: Means a maintenance procedure, practice, condition, etc. that could result in damage or destruction of equipment.

NOTE: Means a maintenance procedure, practice, condition, etc., or a statement which needs to be highlighted

GENERAL ADVISORIES

NOTE: These instructions are intended for use by personnel familiar with standard aircraft avionics

practices and methods of maintenance. If you do not have prior experience with or knowledge of avionics

systems, do not attempt the following instructions. FreeFlight Systems will not be held liable for damaged

items resulting from improper handling and maintenance.

WARNING

Service personnel are to obey standard safety precautions, such as wearing safety glasses, to prevent

personal injury while installing or doing maintenance on this unit.

WARNING

This FDL-978 Series UAT unit exhibits a high degree of functional reliability. Nevertheless, users must

know that it is not practical to monitor for all conceivable system failures and, however unlikely, it is

possible that erroneous operation could occur without a fault indication. The pilot has the responsibility to

find such an occurrence by means of cross-checks with redundant or correlated data available in the

cockpit

Capstone-ICA-0103

Rev. C 6 of 21

CAUTION

Remove all power to the FDL-978 Series UAT unit before disconnecting or removing it. Disconnecting

the unit with power connected may cause voltage transients that can damage the unit.

NOTE

Superseded Documents: The information, procedures, requirements, and limitations contained in this

Instructions for Continued Airworthiness for this type design change supersede the information,

procedures, requirements and limitations contained in the airplane’s maintenance manual when the type

design change is installed on the Type Certificate Holder’s airplane.

NOTE

“On Condition”: On condition means a unit or system has no scheduled maintenance or inspections and

are only repaired when a fault is noted by the system or pilot.

NOTE

Maintenance and design changes to interfacing components. The ADS-B system interfaces with

multiple external components, such as position sources and altimetry sources. All interfacing components

are listed in the Equipment List, in Section 24 of this document. It is important that any future

maintenance or design changes to these interfacing components be accomplished in such a way that

continued satisfactory performance of the overall ADS-B system is maintained.

4.1 Purpose

The purpose of this Continued Airworthiness Maintenance Plan is to provide the line maintenance

technician with the information necessary to ensure the continued airworthiness of the FDL-978 Series

UAT ADS-B systems.

NOTE: These STC approved ICA do not include details for the continued airworthiness of new air data,

pressure altitude sensors, GPS, multifunction displays or other ADS-B supporting systems. These

“existing” systems were previously installed / FAA approved or were installed and FAA certified

appropriately concurrently to interface with new ADS-B system covered by these ICA. For details of

other systems refer to appropriate ICA of that system.

4.2 Effectivity

This maintenance plan is effective for all aircraft with FFS FDL-978 Series UAT ADS-B system installed

in accordance with FreeFlight Systems Report No. Capstone-AML-0103 Approved Model List for ADS-

B System installed in Approved Model List Aircraft This maintenance plan is designed to meet the

required INSTRUCTIONS for CONTINUED AIRWORTHINESS (14 CFR FAR 23.1529), for aircraft

equipped with the FFS FDL-978 Series UAT ADS-B system. This plan must be placed into the aircraft

operator’s Aircraft Maintenance Manual and incorporated into the operator’s scheduled maintenance

program.

Capstone-ICA-0103

Rev. C 7 of 21

4.3 Part Number Equivalency

FreeFlight Systems sells the FDL-978 series ADS-B Systems and other parts associated with this STC to

other avionics manufacturers, rebranded as their own product. Refer to Capstone-QPL-0103 for Part

Number cross-reference.

4.4 Reference Documents

FreeFlight FDL-978 GPS/WAAS Installation Manual (87343, Rev A or later).

FreeFlight WI-FI Installation/operations Manual (87330, Rev - or later).

FreeFlight FTC-190CTransponder Monitor Installation/operations Manual (87114, Rev - or

later).

Wiring Diagram, CS-0103-WD

Structural Diagrams CS-0103-SEN, CS-0103-ANT, and CS-0103-RT.

Capstone-QPL-0103 Qualified Parts List

4.5 Applicable FAR

FAR 23.1529 Instructions for Continued Airworthiness

FAR 43.16 Airworthiness Limitations

FAR 91.403 General

5 GENERAL

Maintenance technicians should thoroughly familiarize themselves with ADS-B System installation,

wiring interface, and system operation, prior to attempting to maintain or troubleshoot this system.

5.1 GENERAL WIRING INSTRUCTIONS

When using this manual always also follow acceptable avionics installation practices per FAA Advisory

Circulars AC 43.13-1B (Chapters 1, 2, 3, 11, 13) Acceptable Methods Techniques and Practices-Aircraft

Alteration, AC 43.13-2B (Chapters 1, 2, 3, 11) Acceptable Methods Techniques and Practices-Aircraft

Alteration, SAE AS50881 Wiring Aerospace Vehicle (Chapters 3-1 through 3-24, 6-1 through 6-8), SAE

ARP1870 (Chapters 4,5) Aerospace Systems Electrical Bonding and Grounding for Electromagnetic

Compatibility and Safety. Always use latest FAA accepted revisions of these documents.

5.2 Wire Separation

Whenever it becomes necessary to repair or replace a wire or group of wires, maintain the same aircraft

manufacturers wire separation that was used to install the system and follow guidance noted above. Any

wire added to or removed from the aircraft should satisfy aircraft manufacturers design philosophy

regarding separation requirements and wiring standards. Refer to Wire Routing FFS ADS-B Drawing No.

CS-0103-RT and noted reference data for wire separation requirements for ADS-B system wiring

5.3 Wire Routing

Whenever it becomes necessary to repair or replace a wire or group of wires, maintain the same wire routing

that was used to install the system and follow guidance noted above. Wires should be routed using proper

bend radius, drip loops, slack and to allow for easy access for maintenance repairs and inspection. Route

wires in such a manner that it does not violate any regulatory safety requirements or Aircraft Manufacturer’s

wire routing maintenance manual guidance. Refer to Wire Routing FFS ADS-B Drawing No. CS-0103-RT

and noted reference data (Para 5.1 above) for repair and routing of ADS-B system wiring.

.

Capstone-ICA-0103

Rev. C 8 of 21

5.4 Securing Wire Bundles

Whenever it becomes necessary to repair or replace a wire or group of wires, clamps of the proper size,

type, and material should be used. Secure repaired or replaced wiring in the same manner that it was

installed in the aircraft. Refer to Wire Routing FFS ADS-B Drawing No. CS-0103-RT and noted reference

data for repair and routing of ADS-B system wiring.

5.5 Wire Termination

Whenever it becomes necessary to terminate wires, care should be taken to ensure enough slack in wiring

for proper servicing, repair, and fit. When stripping wires for termination, be sure not to nick or cut strands

of wire. Check that proper crimping tools are used, and that they are set to the proper setting for a correct

crimp. When crimping terminals and/or splices use correct size for the wire gauge. If soldering is necessary

be sure a cold solder joint does not exist, and that shrink tube of the proper size is installed over the wire

and connection point.

NOTE: It is expected that the skilled technicians performing the inspections, test, and

troubleshooting of the FDL-978 Series ADS-B System, will adhere to the safety practices

and operational procedures given in the basic aircraft manufacturers Maintenance

Manuals.

6 System Description

The FDL-978 series is designed to share aircraft position, velocity, and other flight data with other aircraft and

ground station equipment through ADS-B IN and ADS-B OUT services. The FDL-978 satisfies the TSO

requirements and the associated MOPS for UAT ADS-B class A1H/A1S equipment for ADS-B OUT. The FDL-978

collects position, velocity, and other aircraft information from an aircraft GPS, pressure altitude sensor, and pilot

interface controller and transmits this data out once per second. The GPS data, pressure altitude data, and pilot

control inputs are received by the FDL-978 through configurable RS-232/422/485 serial, ARINC 429 serial, and/or

discrete interfaces. Status information about the FDL-978 health and state are output on the configured serial links

and/or discrete signals for display to the pilot. Traffic and weather data can be displayed to the pilot when ADS-B

IN services are available.

The FDL-978 series has three main categories, XVR, TX, and RX. The XVR allows both ADS-B IN and ADS-B

OUT, whereas the TX only allows ADS-B OUT, and the RX allows ADS-B IN.

For information only, Figure 1 shows a block diagram of a generic FDL-978-XVR installation. This

installation shows the TC978 Front Panel Controller, the FDL-978-XVR Transceiver, two UAT antennas,

a GPS/WAAS sensor, and a GPS antenna. The GPS sensor can be an existing aircraft GPS source if it

meets the interface requirements of the FDL-978-XVR (FFS Navigation Interface Protocol (RS-232 or

RS-422) such as the FFS 1201 or ARINC 743A compatible GPS (e.g. 1203/1203C) through an ARINC

429 bus.

The TC978 Controller contains an TSO-C88b/ETSO-C88a certified pressure altitude encoder and a

RS-232 serial output to share the altitude encoder data with other devices such as a transponder.

Additionally, an Air Data System or Pressure Altitude Sensor can optionally be interfaced to the FDL-978

to provide pressure altitude, altitude rate, and true airspeed if it meets the interface requirements of the

FDL-978. If an optional ADS or Altitude Sensor is configured with the FDL-978, the TC978 Controller

Capstone-ICA-0103

Rev. C 9 of 21

will display the optional sensor altitude and output the optional altitude data on its RS-232 serial output.

Note that the Transponder and the FDL-978 must share the same pressure altitude sensor data.

Capstone-ICA-0103

Rev. C 10 of 21

An FTM-190C Transponder Monitor (or internal transponder monitor function) will also be installed to allow the

ADS-B system to interface with existing “analog” transponder systems for mode and select functions. The TC-978

controller is a screw mounted LRU and is located in the aircraft Cockpit. The TC-978 controller functions for the

ADS-B system control/code selection only and is also designed to interfaced with existing aircraft transponder

controls to operate in a “slave” control (single point of entry mode 3A) for mode / code / Ident entry under normal

operating conditions. In the rare case of transponder fault the TC-978 both annunciates the fault and assumes control

of the ADS-B system.

The system currently is not interfaced with a TCAS II or Heading system.

System electrical power will be obtained from the aircraft essential bus / battery bus supplying 12/14Vdc or 28 Vdc

(ADS-B system power requirement10-40 Vdc) as applicable to a particular aircraft model. The system is interfaced

with existing aircraft Air data Computers via RS232, RS422, or RS485 digital bus (Ref wiring diagram CS-0103-

WD) as previously installed for Barometric Altitude. This ADS-B altitude source used is the same source providing

altitude input to the transponder for reporting purposes. An interface to the aircraft L-band antenna RF suppression

system is also included. As noted, no heading input, TCAS or other system interfaces are included and the

installation does not add additional controls, switches, annunciators, or other sensors.

The GPS and FDL 978 system installation will include required antennas located top and bottom of the aircraft near

centerline, installed in accordance with design data listed on Master Data List Capstone-MDL-0103. The FDL 978

ADS-B will be installed in accordance with design data listed on Master Data List Capstone-MDL-0103.

Figure 1 Typical FDL-978-XVR Installation

The FDL-978 Lite Series provide limited connectivity to peripheral systems.

Capstone-ICA-0103

Rev. C 11 of 21

6.1 1201 GPS/WAAS (When installed)

The FFS 1201 GPS/WAAS is a Twelve-channel receiver, L1 frequency, C/A code, continuous

tracking Nine GPS, 2 WAAS, 1 overhead, satellite capability sensor. The system will include a

single TSO-C145a antenna located at centerline top forward fuselage, installed in accordance

with design data listed on Master Data List Capstone-MDL-0103

6.2 SYSTEM COMPONENTS

The FDL-978 Series UAT ADS-B system does not require forced-air cooling. The tray can be

installed in a variety of locations, such as the electronics bay, under a seat or behind the rear baggage

area. Refer to FreeFlight Equipment Installation drawing number CS-0103-SEN for suggested

locations. Sufficient clearance is left between the FDL-978 Series UAT ADS-B system and any

obstruction for ease of maintenance. Tray in generally installed in accordance with AC 43.13-2B

Chapter 2 Communication, Navigation, and Emergency Locator Transmitter System Installations

(refer to FreeFlight Equipment Inst’l drawing number CS-0103-SEN).

The FDL-978 Series UAT ADS-B system chassis must always have a ground path to the airframe by

having at least one mounting screw in direct contact with the airframe.

If the Personality Module (PM) should need to be replaced do so by simply stripping the leads and

crimping the contacts. Do not extend the length of the PM wires.

The PM is secured by adhering one side of the double sided tape to the PM and the other side to one

side of the connector backshell as the connector and backshell are assembled together.

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Rev. C 12 of 21

The system consists of the following components

Part Number Description Vendor

87098-00 FDL-978-XVR (Internal GPS) FreeFlight Systems

87098-10 FDL-978-XVR (External GPS required) FreeFlight Systems

87098-00-FX00 FDL-978-XVR (Internal GPS) FreeFlight Systems

87098-10-FX10 FDL-978-XVR (External GPS required) FreeFlight Systems

87098-00-FR00 FDL-978-RX (Internal GPS) FreeFlight Systems

87098-10-FR10 FDL-978-RX (External GPS required) FreeFlight Systems

87098-00-FX0L FDL-978-XVR Lite (Internal GPS) FreeFlight Systems

87098-00-FT0L FDL-978-TX Lite (Internal GPS) FreeFlight Systems

87349 TC-978 UAT Controller FreeFlight Systems

85945-00-A Personality Module FreeFlight Systems

84100-03-0306 1201 GPS/WAAS Sensor FreeFlight Systems

81194 GPS/WAAS Antenna FreeFlight Systems

87005 L Band “blade” antenna FreeFlight Systems

86943-00 Serial-to-WiFi Aircraft Module FreeFlight Systems

Table 6-1 LRU PARTS LIST

7 Control and Operation Information

7.1 Controls (Existing, Added)

The transponder is controlled via the existing aircraft Transponder Control. This existing control also

provides mode 3A codes to added FDL-978-XVR/L or TX/L ADS-B system (under normal conditions, mode

3A override function provided for operation during transponder faults). The ADS-B system on-off is

controlled via TC-978 control when installed. This control is not required for the FDL-978-RX.

7.2 Displays

This installation is standalone and includes display of information on existing aircraft multifunction

displays.

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Rev. C 13 of 21

8 SERVICING INFORMATION

8.1 TRANSPONDER

The existing Transponder does not require additional scheduled maintenance or calibration as a result of

added ADS-B system. Requirements under 91.411 and 91.413 requirements are unchanged by ADSB

system installation reference FAR Part 43, Appendix E, Altimeter System Test and Inspection, FAR Part

43, Appendix F, ATC Transponder Tests and Inspections.

8.2 1201 GPS/WAAS (When installed)

The 1201 GPS/WAAS does not require scheduled maintenance or calibration. If overhaul is required it

shall be “on condition”. Additionally, there are NO software field or database updates required or to be

performed for the 1201 GPS/WAAS.

8.3 FDL-978 Series UAT ADS-B system

The FDL-978 Series UAT ADS-B system transceiver does not require scheduled maintenance or

calibration. If overhaul is required it shall be “on condition”

8.4 FTM-190C Transponder Monitor (When installed)

The FTM-190C transponder monitor does not require scheduled maintenance or calibration. If overhaul

is required it shall be “on condition”

8.5 TC-978 ADS-B Controller (When installed)

The TC-978 ADS-B Controller does not require scheduled maintenance or calibration. If overhaul is

required it shall be “on condition”

8.6 WI-FI (When installed)

The WI-FI module does not require scheduled maintenance or calibration. If overhaul is required it shall

be “on condition”

8.7 FDL978 Series UAT ADS-B SYSTEM ADS-B, 1201 GPS/WAAS SYSTEM SOFTWARE

The FDL978 Series UAT ADS-B system AND 1201 GPS/WAAS require no aircraft level software

maintenance considerations. Any follow on software updates will be performed strictly in accordance

with Equipment Manufacturer’s approved Service Bulletins.

9 MAINTENANCE INSTRUCTIONS

9.1 General

Maintenance of the ADS-B system is “On-Condition” and does not require new maintenance or

inspection action unless a system fault is detected. However, this “on condition” requirement does not

override any inspections that might be required during any Continuous Inspection Program for a given

aircraft. On-Condition and / or airworthiness inspections required under FAR Part 43, or other FAA

approved programs, should include several items regarding the ADS-B System installed in the aircraft.

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Rev. C 14 of 21

9.2 Servicing

Servicing of the ADS-B system is “On-Condition” but should be checked during any Continuous

Inspection Program as a minimum. On-Condition and / or airworthiness inspections required under FAR

Part 43, or other FAA approved programs, should include several items regarding the ADS-B System

installed in the aircraft.

10 Troubleshooting Information

10.1 Internal and External GPS

ADS-B IN-OUT system troubleshooting will be performed as follows:

NOTE: For basic transponder testing refer to applicable manufacturer’s Operation and Installation

Manual.

Note: ADS-B system testing will be accomplished using a FreeFlight Systems (FFS) provided test set

equipment part number 85595-00-MTX to capture the output of the “ADS-B in-out” system. This Test

Set DOES NOT require calibration and testing will be accomplished in accordance with Section 3 of FFS

Equipment Installation Manual 87343, Rev A or later.

Interface/System Functional Testing: The ADS-B system transmits below information. Ground testing

will verify that the interface between each of the onboard systems is accurate, confirms that the internal

GPS/WAAS or external GPS/WAAS position source output to the ADS-B is correct, and that the ADS-B

system transmissions are correct. After power on record/verify the following.

1. Verify that there are no Device Failure (ADS-B Failure) or Function Failure (Position Failure)

indications for ADS-B on the Instrument Panel ________________

2. Record Navigation Integrity Category (NIC) (Minimum Value equal to or greater than 7)

________________

3. Record Surveillance Integrity Level (SIL) (Minimum Value 2) ______ __________

4. Record Navigation Accuracy Category Position (NACp) (Minimum Value equal to or greater

than 8) _ _______________

5. Record Navigation Accuracy Category Velocity (NACv) (Minimum Value equal to or greater

than 1) ________________

6. Record transponder set codes (1200) match ADS-B transmitted codes ________________

7. Confirm Ident function on transponder/ADS-B controller as installed ________________

8. Confirm WI-FI (if installed) module provides output to PED equipment ________________

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Rev. C 15 of 21

10.2 FDL-978 TROUBLESHOOTING PROCEDURE

The following Table is a troubleshooting guide for the FDL-978 Series Systems. The LEDs referred to are on the FDL-978 Line Replaceable Unit:

PROBLEM POTENTIAL CAUSE TROUBLESHOOTING

No LED Activity No power Verify power is turned on,

Check power connections to unit.

Tx LED not active Unit is not transmitting ADS-B messages

Check antenna connections,

Check TC978 Warning messages

Rx LED not active Unit is not receiving ADS-B messages

Check antenna connections,

Check TC978 Warning messages

Status LED is on A fault with the unit Check TC978 Warning messages

Status LED is flashing fast

GPS fault has occurred Check GPS connection/configuration, Check TC978 Warning messages

GPS LED is flashing slowly

GPS is acquiring satellites Allow 2-3 minutes for GPS tracking,

Check GPS antenna,

Check GPS for problems

GPS LED is off GPS not communicating Check GPS connection,

Check installation configuration

GPS LED is flashing fast

GPS is reporting a fault Check GPS for fault

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Rev. C 16 of 21

11 Removal and Replacement Information ADS-B antennas and equipment are located in accordance with FreeFlight Systems Drawing No’s CS-

0103-ANT (antennas) and CS-0103-SEN (1201 Sensor, UAT and Control Head) (Drawings reference

Appendix A attached). The components are removed / installed with basic hand tools (screw drivers,

wrench, or socket). Access is gained through aircraft manufacturer’s procedures defined in applicable

Maintenance Manual.

Removal/Replacement of ADS-B components (FDL-978 Series UAT ADS-B system, WI-FI, FTM-190C)

shall be accomplished with reference to installation drawing CS-0103-SEN (remove, retain 4 each or 6

each MS35207 or MS35206 screws or loosen rack thumbwheel as installed for a given part). For

installation, inspect/clean area of any debris and reinstall removed component hardware or reinsert frame

assembly and tighten retainer thumbwheel, hand tight. Antennas shall be removed/installed with reference

to drawing CS-0103-ANT (remove, retain 2 each MS21042 nuts). For installation, inspect/clean area of

any debris and reinstall antenna using removed nuts. (Drawing reference Appendix A attached).

The 1201 GPS/WAAS is mounted using MS27039, AN960 screws/washers as reflected on drawing CS-

0103-ANT (Drawing reference Appendix A attached). (Remove retain MS27039 screws and AN960

washers). For installation, inspect/clean area of any debris and reinstall antenna using removed hardware.

(Drawing reference Appendix A attached).

The 81194 GPS/WAAS Antenna is mounted using manufacturer supplied hardware (4 each MS24694-

C53 screws) as reflected on drawing CS-0103-ANT (Drawing reference Appendix A attached). Remove,

retain 4 each MS24694-C53 screws. For installation, inspect/clean area of any debris and reinstall antenna

using removed hardware. (Drawing reference Appendix A attached).

NOTE: Re-installation of equipment and antennas shall use specified hardware.

Verify proper operation using the procedure in Interface/System Functional Testing above.

Composite Aircraft

Before starting maintenance, always consider with composites that airframe modifications are totally

dependent on the type of construction used in aircraft manufacture. Carbon fiber will have one type of

instructions, Kevlar another, Honeycomb another, etc. Before starting maintenance refer to included

design data (referenced within) and the list of SAE documents specified below for additional guidance on

a given aircraft type, e.g. AC 43-206 Part 2). Also refer to the aircraft manufacturers Maintenance

Manual, Aircraft Standard Practices and/or Structural Repair Manual whenever there is a conflict between

listed documents. Design drawing requirements always take precedent over all other documents. Any

area not covered must be referred to FFS engineering for disposition.

NOTE

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Rev. C 17 of 21

FAA documents supplementing design data

FAA AC 43-214 ( ) Repairs and Alterations to Composite and Bonded Aircraft Structure (and

guidance referenced within this circular)

FAA AC 20-107 ( ) Composite Aircraft Structure (and guidance referenced within this

circular).

FAA AC 43-206 ()

(Parts 1-2)

Inspection, Prevention, Control, and Repair of corrosion on

Avionics Equipment

Industry Guidance supplementing design data

SAE ARP 5089 Composite Repair NDT/NDI Handbook

SAE ARP 4916 Masking and Cleaning of Epoxy and Polyester Matrix Thermosetting Composite

Materials

SAE AIR 4844B Composites and Metal Bonding Glossary

SAE AIR 4938 Composite and Bonded Structure Technician/Specialist: Training Document

SAE AIR 5278 Composite and Bonded Structure Engineers: Training Document

SAE AIR 5279 Composite and Bonded Structure Inspector: Training Document

SAE AIR 5719 Teaching Points for an Awareness Class on "Critical Issues in Composite Maintenance

and Repair

SAE ARP 4977 Drying of Thermosetting Composite Materials

SAE ARP 4991A Core Restoration of Thermosetting Composite Components

SAE ARP 5143 Vacuum Bagging of Thermosetting Composite Repairs

SAE ARP 5144 Heat Application for Thermosetting Resin Curing

SAE ARP 5256 Mixing Resins, Adhesives and Potting Compounds

SAE ARP 5319 Impregnation of Dry Fabric and Ply Lay-Up

SAE ARP 5605 Solid Composite Laminate NDI Reference Standards

SAE ARP 5606 Composite Honeycomb NDI Reference Standards

In general, for maintenance or repair on nonstructural locations on composite skins each of the

maintenance instructions for drilling, sealing, and ensuring compatible materials for each aircraft must be

followed. Galvanic corrosion must be considered to prevent carbon composites from being in contact

with aluminum. It is preferred that a protective ply of inert cloth such and fiberglass or Kelvar should be

cured between the carbon and aluminum components and properly sealed. If the aluminum is applied

directly to a carbon component all aluminum parts must be anodized per MIL-A-8625, Type II and the

external surfaces of both aluminum and carbon parts use MIL-F-18264, with two coats of epoxy primer

per MIL-P-85582, and two coats polyurethane enamel per MIL-C-83286.

Fasteners used with carbon must be titanium or corrosion resistant steel. Cadmium-plated fasteners may

not be used in carbon composites. All fasteners should be installed wet with a corrosion inhibiting

sealant. Proper use of backing plates and fastener torque must be considered to prevent damage to the

composite during installation.

During maintenance or repair, electrical bonding for EMI, HIRF, Lightning aspects

(bonding/grounding/routing) must be complied with as defined on design data.

For fabric aircraft, the GPS antenna may be located under the fabric and mounted to a bracket that is

clamped to the tube structure. The thickness of the support bracket must be maintained by design for the

span between the tubes but may never be less than 0.032 inch thick 2024-T3 aluminum. For fabric that

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Rev. C 18 of 21

must be penetrated reinforced fabric gussets or grommets must be used depending on the type of fabric.

Care must be taken to properly seal the area for proper UV considerations.

Pressurized Aircraft

Note: When dealing with pressurized fuselages the procedure in the aircraft Maintenance Manual,

Aircraft Standard Practices, or Structural Repair Manual from the OEM are to be complied with for all

drilling, cutting, sealing and other processes. General practices for installation procedures are described in

AC43.13-2A Chapter 3, Paragraph 44 for the fuselage and AC43.13-2A Chapter 13 for cables penetration

a pressurized structure. In all cases the design drawing will take precedent over all other referenced

documents. If required, specific instructions for initial and future inspections will be in the Instruction for

Continued Airworthiness.

In general, installations on pressurized aircraft must consider not only static strength but all fatigue and

damage tolerance requirements for each type of aircraft and location on the aircraft. Skin thickness,

antenna location, fastener and feed through size, drag and handling loads all must be considered in the

design, analysis, and approval. Proper inspection instructions for inspection method and time between

inspections must be added in the Instructions for Continued Airworthiness for each antenna location on a

pressurized aircraft. This applies to not only the antenna location but to any area where the pressure

vessel requires a penetration for wiring or any other reason. Only approved connectors may be used and

each location will require adequate structural design data for fatigue and damage tolerance (see below).

Upon LRU replacement perform above GO-NO GO ground test procedure.

12 Wiring Diagrams (Interface Diagram)

Refer to the wiring diagrams in Appendix A for system integration and wiring information:

13 Special Inspection Requirements

No new inspections required

Note: Special inspections relating to hard landing and or lightning strike for the GPS antenna and Sensor

will be done in accordance with existing aircraft manufacturer’s instructions.

14 Application of Protective Treatments

Not Applicable

15 Data for Structural Fasteners

None.

16 List of Special Tools

None, antennas and equipment are removed and installed with basic hand tools

17 Commuter Category Aircraft

N / A

18 Recommended Overhaul Periods

No additional requirements.

NOTE

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Rev. C 19 of 21

19 Weight and Balance

Weight and Balance change should be addressed in accordance with standard procedures specified in

aircraft Maintenance Manual.

20 Airworthiness Limitations

The Airworthiness Limitations section is FAA approved and specifies maintenance required under §§

43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA

approved.

There are no new (or additional) airworthiness limitations associated with this equipment and/or

installation.

Limitation: This STC approved installation does not include authorization for installation or

maintenance of new air data, pressure altitude sensors, GPS, multifunction displays or other ADS-B

supporting systems. These “existing” systems shall be previously installed / FAA approved or will be

installed and FAA certified appropriately prior to interface with new ADS-B system. These existing

systems ICA are not altered as a result of ADS-B installation but should be referenced as/if required when

using this manual for maintenance.

Limitation: This STC does not authorize ADS-B installation in an aircraft with existing 8.33 Khz

spacing VHF transceiver(s) unless additional frequency EMI immunity testing has been accomplished as

specified in Capstone-GTP-0103 test procedure. This additional EMI testing shall be as specified and

agreed with/coordinated through ACO.

If an 8.33 Khz spacing transceiver(s) are to be installed after installation of this STC the above testing and

coordination with ACO is required before installation of transceivers and aircraft return to service.

21 Structural Inspections:

No structural inspections required.

22 Annual Inspections:

No new annual inspections required Note: Annual inspections relating to hard landing and or lightning strike for the GPS antenna and Sensor

will be done in accordance with existing aircraft manufacturer’s instructions.

23 Revisions

For the latest revisions of all STC documents, contact FreeFlight Systems @ 254-662-0000.

Capstone-ICA-0103

Rev. C 20 of 21

24 Installed Equipment List

This table shows the ADS-B system installed on this aircraft and the associated peripheral devices. This

table is to be completed by the installing agency. When installing or upgrading equipment that interface

with the ADS-B system, this table should be updated. ADS-B (UAT) System Part Number

The ADS-B (UAT) type

installed in this Airplane:

The Installed ADS-B (UAT) Equipment Installed in

this Airplane and Type of System:

ADS-B Type:

ADS-B OUT ADS-B IN

ADS-B IN and OUT

Encoder/Digitizer Model:

Peripheral Device For

ADS-B OUT Peripheral Device Installed in this Airplane: Part Number

1.

Dedicated ADS-B

OUT UAT Controller

for Airplanes Without

an Onboard 1090MHz

Transponder:

Dedicated ADS-B OUT UAT Controller Installed in

this Airplane:


Aspen EFD1000 PFD

Garmin MX20 MFD

Garmin GMX 200 MFD

Garmin GSL 71 UAT Control Panel

Not Available

2.

Separate ADS-B OUT

UAT Controller used

for temporary control

when the non-digital

Transponder is Not

Interrogated by a

Ground Station:

ADS-B OUT UAT Controller Installed in this

Airplane:


Aspen EFD1000 PFD

None - The UAT is always controlled

simultaneously by the digital onboard transponder.

Not Available

3. ADS-B OUT UAT

Annunciator:

ADS-B OUT UAT Annunciator Type Installed in this

Airplane:


Aspen EFD1000 PFD

Garmin MX20 MFD

Garmin GMX 200 MFD


Panel Annunciator (“ADS-B” in amber)

Not Available

Capstone-ICA-0103

Rev. C 21 of 21

Table 2 Installed Equipment List, continued

Peripheral Device for

ADS-B IN Peripheral Device Installed in this Airplane: Part Number:

4. ADS-B IN Traffic

and FIS-B Display:

Traffic and FIS-B Display Installed in this Airplane:

Aspen EFD1000 PFD

Aspen EFD1000 MFD

Aspen EFD500 MFD

Garmin MX20 MFD

Garmin GMX 200 MFD


None - Wi-Fi Module only

Not Available

5.

ADS-B IN Traffic

Only (Proximity

Traffic’ and ‘Other

Traffic’ symbols.

There are no Traffic

Alerts)

Garmin ADS-B IN (Traffic Only) Installed in this

Airplane:



Not Installed

6.

Wi-Fi Module:

(used with ADS-B

IN)

FreeFlight Wi-Fi Module Installed in this Airplane:

Installed

Not installed

Not available

Peripheral Device for ADS-

B IN, ADS-B OUT or both Peripheral Device Installed in this Airplane:

Part Number when

applicable

7. External GPS Type:

ADS-B IN and/or OUT External GPS Type Installed in

this Airplane:

FreeFlight Systems Model 1201 GPS



None (internal GPS)

8. Air-Ground Status

Determination

ADS-B IN and/or OUT Air-Ground Status

Determination on this Airplane:

Discrete signal using airspeed

Discrete signal using weight-on wheels

Determined internally in the FreeFlight System

Installer: ________________________________ Date: _________________________________

25 Appendix A (Drawings) Note to the Installer

a. Prepare and insert a Wiring Diagram titled, “Wiring Diagram for (insert the serial number and

Registration Number of the airplane)” for the FreeFlight ADS-B Modification for the

modification to this airplane here.

b. Insert a drawing after the wiring diagram depicting the locations of the Installed Equipment titled,

“Installed Equipment Locations for (insert the serial number and Registration Number of the

airplane)” for the modification to this airplane.