Wire Harness overbraid is required for. IFR Installations. Reference the. Installation Manual for installation requirements. 43. Diamond. Aircraft.
FAA Approved Airplane Flight Manual Supplement (AFMS) with Collins ... AeroNav 780, 800, 880, 900, 905 and 910 Series Navigator model names ...
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Honeywell International, Inc. 9201-B San Mateo Blvd N.E. Albuquerque, New Mexico 87113 USA. CAGE: 6PC31 Telephone: 855-250-7027 (Toll Free U.S.A./Canada) Telephone: 602-365-7027 (International Direct) Website: www.bendixking.com
AeroNav 780/8XX/9XX Integrated Flight Deck Navigator Series
AML STC Document for Part 23 Aircraft
STC Number SA00343BO
The attached documents are distributed by BendixKing to provide technical support for installation of the Honeywell International, Inc. AeroNav 780/8XX/9XX IFD Navigator Series using AML STC Number SA00343BO.
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
Publication Number D201907000026, Revision 000
Page T-1 Initial 29 JUL 2019
© Honeywell International Inc. Do not copy without express permission of Honeywell.
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Revision (-)
Initial release
DOCUMENT REVISIONS
Description of Change
DATE 29 JUL 2019
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TABLE OF CONTENTS AeroNav 780/8XX/9XX IFD Navigators Letter of Model Designation ................ Page 4 FAA Supplemental Type Certificate (STC) SA00343BO, March, 06, 2017 ....... Page 6 EASA Supplemental Type Certificate (STC) 10058132, August 4, 2017 .......... Page 10 Canada Supplemental Type Certificate (STC) SA14-78, June 23, 2016........... Page 21 Mexico Certificado de Tipo Suplementario (STC) IA-486/2018, February 26, 2018 ............................................................................................. Page 47 ANAC Certificado Suplementar De Tipo (STC) 2014S12-04, April 10, 2017 .... Page 51 CAAC Supplement Type Certificate (STC) VSTC0887, November 08, 2018.... Page 62 FAA Approved Model List (AML), May 9, 2019 ................................................. Page 63 EASA Approved Model List (AML), April, 11, 2018 ........................................... Page 81 Master Document List (MDL), April 17, 2019 .................................................... Page 96 FAA Approved Airplane Flight Manual Supplement (AFMS), May 03, 2019 ..... Page 102 EASA Approved Airplane Flight Manual Supplement (AFMS), May 03, 2019... Page 128 FAA Approved Airplane Flight Manual Supplement (AFMS) with Collins ProLine 21 Avionics, May 03, 2019 ..................................................................................... Page 151 AML STC Installation Manual (IM), April 17, 2019 ............................................ Page 178 Instructions for Continued Airworthiness (ICA), April 17, 2019.......................... Page 437 EASA Installation Checklist, September 7, 2017............................................... Page 457
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BendixKing 9201-B San Mateo Blvd, NE Albuquerque, NM 87113
Subject: AeroNav 780 / 8XX / 9XX IFD Navigator Series Letter of Model Designation for Avidyne IFD4XX & IFD5XX Navigators
This letter of model designation is intended to provide the limited purpose of associating the BendixKing AeroNav 780, 800, 880, 900, 905 and 910 Series Navigator model names with the Avidyne IFD 410, IFD440, IFD510, IFD540, IFD545, and IFD550 Navigators, respectively, autopilot that is manufactured for Honeywell and BendixKing by Avidyne. Refer to the Cross Reference of BendixKing Part Numbers to Avidyne Part Numbers table below for a mapping of the Avidyne part numbers to the BendixKing part numbers.
This letter of model designation does not replace any terms of the letter of authorization "LOA" for the Avidyne IFD4XX & IFD5XX Navigators and simply updates the model name as described above. The recipient shall not use this letter of model designation for any other purpose other than those established under the LOA provided to the recipient.
Without prejudice to this letter of model designation, authorization to use the AeroNav 780, 800, 880, 900, 905 and 910 Series Navigator names or any portion thereof may not be assigned or sub-licensed by recipient without the express written consent of BendixKing or Honeywell. Additionally, BendixKing's general conditions of purchase apply to this letter as if fully included herein and to all purchases of the AeroNav 780, 800, 880, 900, 905 and 910 Series Navigator.
Sincerely,
BendixKing
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Table 1 Cross Reference of BendixKing Part Numbers to Avidyne Part Numbers
Avidyne P/N
700-00182-700 700-00182-701 850-00182-700 850-00182-701 850-00188-002 850-00188-003 700-00182-730 700-00182-731 850-00182-730 850-00182-731 700-00182-720 700-00182-721 850-00182-720 850-00182-721 700-00179-700 850-00179-700 850-00184-002 850-00184-003 700-00182-710 700-00182-711 850-00182-710 850-00182-711 700-00179-710 850-00179-710
Description
IFD540 (Black Bezel) IFD540 with Video (Black Bezel) IFD540 Ship Kit (Black Bezel) IFD540 Ship Kit with Video (Black Bezel) IFD5XX Fixed Wing Tray and Install Kit IFD5XX Helicopter Tray and Install Kit IFD545 (Black Bezel) IFD545 with Video (Black Bezel) IFD545 Ship Kit (Black Bezel) IFD545 Ship Kit with Video (Black Bezel) IFD550 (Black Bezel) IFD550 with Video (Black Bezel) IFD550 Ship Kit (Black Bezel) IFD550 Ship Kit with Video (Black Bezel) IFD440 (Black Bezel) IFD440 Unit Ship Kit (Black Bezel) IFD4XX Fixed Wing Tray and Install Kit IFD440 IFD4XX Helicopter Tray and Install Kit IFD440 IFD510 (Black Bezel) IFD510 with Video (Black Bezel) IFD510 Ship Kit (Black Bezel) IFD510 Ship Kit with Video (Black Bezel) IFD410 (Black Bezel) IFD410 Unit Ship Kit (Black Bezel)
BendixKing P/N
89000039-001 89000039-002 89000039-003 89000039-004 89000039-007 89000039-009 89000039-013 89000039-014 89000039-011 89000039-012 89000040-001 89000040-002 89000040-003 89000040-004 89000041-001 89000041-002 89000041-005 89000041-007 89000041-012 89000041-013 89000041-009 89000041-010 89000045-001 89000045-003
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SCT
SECRETARiA DE C:OMUN ICAClONlS
y TRANSPOR.TES
Subsecretaría de Transporte Dirección General de Aeronáutica Civil Dirección General Adjunta de Aviación
Convalidación IA-486/2018 del Certificado de Tipo Suplementario No. SA00343BO
La Secretaría de Comunicaciones y Transportes, con base en la Carta de Política AV-01/02 R4, de fecha 24 de Enero de 2012, y al Artículo 21, Fracción XIV del Reglamento Interior de la Secretaría de Comunicaciones y Transportes, a través de la Dirección General de Aeronáutica Civil, otorga este documento a favor de:
The Secretaría de Comunicaciones y Transportes, based in the Carta de Política AV-Ol/02 R4, dated January
24, 2012, and th e Artic/e 21, Section XIV of the Reglamento Interior de la Secretaría de Comunicaciones y Transportes, by means ofthe Dirección General de Aeronáutica Civil, issues this document to:
AVIDYNE CORPORATION 4 Middlesex Green, Suite 221 561 Virginia Road Concord, Massachusetts 01742 USA
Convalidando el Certificado de Tipo SuplementariC? No. SA00343BO, expedido el 24 de julio de 2014, enmendado por última vez el 06 de marzo de 2017, por la Administración Federal de Aviación (FAA) .
Validating the Supplemental Type Certificate No. SA00343BO, issued onJuly 24,2014, amended last time on . March 06, 2017, by the FederalAviationAdministration (FAA).
Lo enunciado a continuación, reúne las especificaciones aplicables para su operación segura de acuerdo con las Normas, Procedimientos y Reglamentaciones requeridas por esta Dirección General de Aeronáutica Civil (DGAC).
The described be!ow meets the applicable specifications jor scife operation in accordance with the Standards, Procedures and R egulations required by the Dirección General de Aeronáutica Civil (DGAC).
Bl,.d. ,\ddJo [,ópezl'vL\{'.'(lb #1990. Ct:,j. Ij)s Alpes Tlacop:K, l.lekgación /\lvetn) Obregón, Ciudad de JVléxíco, c.P. 01010. Página 1 de 4
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SECRETARiA I)f COMUNICACIONI:S
y TMNSI'ORTES
No. control DGAC DGAC control No. Titular / Holder
IA-48612018 Avidyne Corporation
Modificación Modification
Instalación de una configuración simple o de una configuración dual de Display de Vuelo Integrado, Modelo IFD5XX y/o Modelo IFD4XX, de Avidyne Corporation, cargado con el lanzamiento del software 10.2 (o lanzamiento posterior aprobado por la FAA), de acuerdo con Lista Maestra de Documentos (MDL) de Avidrne Corporation, Documento No. AVIFD-306, revisión 11, de fecha 28 de febrero de 2017, o revisión posterior aprobada por la FAA.
Limitaciones y Condiciones Limitations and Con ditio ns
Installation of a single corifiguration or of a dual configuration Avidyne Corporation
Integrated Flight Display, Model IFDSXX and/or Model IFD4xx, loaded with Release 10.2 software (or later FAA approved release), in accordance with Avidyne Corporation Master Document List (MDL), DocumentNumber AVIFD-306, Revision 11, dated February 28,2017, or later FAA approved revision. 1. La operación debe llevarse a cabo de acuerdo con el Suplemento al Manual de Vuelo de la Aeronave (AFMS), Documento No. 600-0298-000, Revisión 05, aprobado por la FAA el 06 de marzo de 2017, o revisión posterior aprobada por la FAA. El AFMS debe llevarse a bordo de la aeronave durante todos los vuelos.
2. El mantenimiento debe efectuarse de acuerdo con las Instrucciones de Aeronavegabilidad Continua (ICA), Documento No. AVIFD-315, Revisión 08, de fecha 18 de enero de 2017, o revisión posterior aceptada por la FAA. Las ICA deben estar disponibles para el operador al momento de la instalación.
3. Los software aprobados compatibles para el IFD4XX e IFD5XX están identificados en el manual de instalación indicado en la MDL aprobada.
4. El Modelo IFD4XX y/o el Modelo IFD5XX pueden interactuar solo con sistemas probados de aviónica compatibles como se identifican por nombre de vendedor y número de modelo, en la sección 2.3 del Manual de Instalación de Avidyne Corporation, Documento No. 600-00299-000, Revisión 04, de fecha 09 de abril de 2015, o revisión posterior aprobada por la FAA.
I\lvd. Ad"U(> L,ópcz;'vLlI(,o> #1.990. Cl!. L.os Alpc> TlaCOP;K, I)dq;~\ci(Ín Alv'lr<> ObrcgtÍn, Ciudad de ;Vlexico, c.p, 01010.
Página 2 de..j
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SECRETARIA [)F COMUNICACIONES
Y TRANSPORTES
No. control DGAC DGAC control No.
IA-486/2018
Limitaciones y
5. La compatibilidad de este diseño con modificaciones previamente aprobadas
Condiciones
debe ser determinada por el instalador.
(Cont.) Limitations and Conditions M odification
6. Cualquier enmienda al STC No. SA00343BO, por parte de la FAA, deberá ser notificada por la FAA a esta DGAC para efectos de actualización de la presente convalidación.
(Co nt.)
1. Operation must be in accordance with the Avidyne Corporation Aircraft Flight
Manual Supplement (AFMS) Document Number 600-00298-000, Revision 05, FAA
approved on March 06, 2017, or later FAA approved revision.
The AFMS must be carried in the aircraft during alljlights.
2. Maintenance must be in accordance with Instructions lor Continued Airworthiness (ICA), Document Number AVIFD-315, Revision 08, datedjanuary 18,2017, or later FAA accepted revision. The lCA must be made available to the operator at the time ofinstallation.
3. The compatible approved software for the IFD4XX and IFD5XX are identified in the installation manual identified on the approved MDL.
4. Model IFD4XX and/or Model IFD5XX can interface only with proven compatible avionics systems as identified by vendor name and model number in Avidyne Corporation Installation Manual Section 2.3, Document Number 600-00299-000, Revision 04, datedApril09, 2015, or later FAA approved revision.
5. Compatibility of this design with previously approved modifications must be determined by the installer.
6. Any amendment to STC No. SA00343BO by the FAA, must be notified by the FAA to the DGACfor update purposes ofthis validation.
IIh<l. :\j"jl~, j,'ípu;'vLHl'(lS #J990, C()l.l..o~ Alpc, TlaCOpCic, lldcf.;ación /íJvaro Obrl~f.;Ón, Ciudad de ,Vlé.xico, c.p, mOlO . Pá¡:''Ína 3 ele 4
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No. control DGAC DGAC control No.
IA-48612018
Aplicable a las
Ver la Lista de Modelos Aprobados por la FAA (AML), Documento No.
aeronaves
A VIFD-318, Revisión 03, aprobada por la FAA el 06 de marzo de 2017, o revisión
Applicability
posterior aprobada por la FAA, para la lista de modelos de aeronaves aprobadas,
los requerimientos de información para la instalación aplicables, y las limitaciones
específicas.
See the FAA Approved Model List (AML), Document No. AVIFD-318, Revision 03,
FAA approved on March 06, 2017, or later FAA approved revision, for the list of
approved airplane models, applicable installation data requirements, and specific limitations.
VIGENCIA: Esta convalidación se mantendrá vigente hasta que sea cancelada, suspendida o revocada o si se establece una fecha de terminación por la Dirección General de Aeronáutica Civil (DGAC).
Validity: This v.al idation shall remain in effect until surrendered, suspended or revoked or a termination date is otherwise establish ed by the Dirección General de Aeronáutica Civil (DGAC).
FECHA DE EMISIÓN Date ofIssue
26 de febrero de 2018 February 26, 2018
Di,?
eml Adjunto de Aviación
Eh,!, ':\d"U" .Lópcz],vIar('o; #[990, C"L L.,os Alpc) Tlacop,ll, Ddcg",\Ción Ií.Jvaro Obregón, Ciudad dc lVlb:ico, Cl) 01010, Página ..¡ de .(
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CERTIFICADO SUPLEMENTAR DE TIPO
(Supplemental Type Certificate)
NÚMERO: 2014S12-04
(Number)
Este Certificado, emitido com base na Lei n° 7565 "Código Brasileiro de Aeronáutica", de 19 de dezembro de 1986,
This Certificate, issued in the basis of the Law No 7565 "Código Brasileiro de Aeronáutica", dated 19 December 1986,
é conferido ao (à):
is granted to:
Avidyne Corporation 55 Old Bedford Road Lincoln, MA 01773 USA
por ter a modificação ao projeto de tipo do produto abaixo citado, observadas as limitações e condições
for having the change to the type design of the product mentioned below, with the limitations and conditions
especificadas, satisfeito aos requisitos de aeronavegabilidade aplicáveis.
conditions there for as specified hereon, met the applicable airworthiness requirements.
Produto Original - Número do Certificado de Tipo: * See attached ANAC Approved Model List (AML), Original Product - Type Certificate No: Rev. 02, dated 10 Apr. 2017, or later approved revision. Fabricante: *
Manufacturer:
Modelo(s): *
Model (s):
DESCRIÇÃO DA MODIFICAÇÃO AO PROJETO DE TIPO:
D e s c r i p t i o n o f T y p e D e s i g n C h a n g e:
Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, model IFD5XX and/or model IFD4XX, loaded with Release 10.2 software (or later approved release), in accordance with the Avidyne Corporation Master Document List, Document No. AVIFD-306, Rev. 11, dated 28 Feb. 2017, or later approved revision.
This CST validates in Brazil the STC No. SA00343BO, issued by FAA (USA).
LIMITAÇÕES E CONDIÇÕES:
Limitations and Conditions:
See continuation sheet for applicable data.
DATAS:
Dates of:
Do requerimento: 30 July 2014
Aplication:
Da reemissão:
Reissuance:
Da emissão:
Issuance:
Da emenda:
Amendment:
15 Dec. 2014 10 Apr. 2017
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a) Este Certificado e os dados técnicos com base nos quais ele foi emitido são válidos até que sejam cancelados,
(This Certificate and the supporting technical data used for approval shall remain in effect until surrended,
suspensos, revogados ou um prazo limite seja estabelecido pela Agência Nacional de Aviação Civil.
suspended, revoked or a termination date is otherwise established by the Agência Nacional de Aviação Civil.)
b) No caso de transferência de propriedade deste Certificado, o transferente deve preencher o quadro "Endosso
(In case of transfer of the property of this Certificate, the grantor should fill the blanks of
de Transferência", e o adquirente deve enviar este Certificado à Gerência Geral de Certificação de
"Transfer Endorsement", and the transferee must remit this Certificate to the Gerência Geral de Certificação de
Produto Aeronáutico para que seja reemitido em seu nome.
Produto Aeronáutico to permit reissuance of the Certificate in his name.)
ENDOSSO DE TRANSFERÊNCIA
(Transfer Endorsement)
Transfiro a propriedade deste Certificado Suplementar de Tipo para:
(I transfer the property of this Supplemental Type Certificate to:)
ADQUIRENTE
(Transferee)
Nome: .................................................................................................................................................................
(Name:)
Rua: ..................................................................................................................................................................
(Street:)
CEP: .............................
(Zip:)
Cidade: .......................................
(City:)
Estado:.................... País: ................................
(State:)
(Country:)
TRANSFERENTE
(Grantor)
Nome: .................................................................................................................................................................
(Name:)
Rua: ..................................................................................................................................................................
(Street:)
CEP: .............................
(Zip:)
Cidade: .......................................
(City:)
Estado:.................... País: ................................
(State:)
(Country:)
Data de Transferência:
(Date of Transfer:)
Assinatura do Transferente:
(Signature of the Grantor:)
............................................................................................................................. ..............................................................................................................................
Nome: ...................................................................................................................
(Name:)
Cargo: ....................................................................................................................
(Function:)
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Folha de Continuação ao
(Continuation Sheet to)
CERTIFICADO SUPLEMENTAR DE TIPO
(Supplemental Type Certificate)
LIMITAÇÕES E CONDIÇÕES:
Limitations and Conditions:
NÚMERO: 2014S12-04
(Number)
I. The approval of this type design change should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the relationship between this change and any of those other previously approved modifications, including changes in Type Design, will introduce no adverse effect upon the airworthiness of that aircraft.
II. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.
III. Operation must be performed in accordance with FAA approved Aircraft Flight Manual Supplement (AFMS), Document No. 600-00298-000, Rev. 05, approved on 06 Mar. 2017, or later approved revision.
IV. The maintenance of the aircraft shall be performed in accordance with the Instructions for Continued Airworthiness (ICA), Avidyne Corporation Document No. AVIFD-315, Rev. 08, dated 18 Jan. 2017 or later FAA accepted revision. The ICA must be available to the operator at the time of installation.
V. The compatible approved software for the IFD4XX and IFD5XX are identified in the installation manual identified on the approved MDL.
VI. Model IFD4XX and/or model IFD5XX can interface only with proven campatible avionics systems as identified by vendor name and model number in Avidyne Corporation Installation Manual Section 2.3, Document No. 60000299-000, Rev. 04, dated 09 Apr. 2015, or later FAA approved revision.
VII. The Certification Basis for parts changed or affected by this change, as specified on the FAA STC No. SA00343BO is applicable.
VIII. A copy of this Certificate, the Supplement referred in item III above and the ANAC Approved Model List (AML) for CST No. 2014S12-04 shall be maintained as part of the permanent records for the modified aircraft.
IX. Amended on 23 Dec. 2014 to include the items 108 through 114 in the ANAC Approved Model List (AML) for CST No. 2014S12-04.
X. Amended on 04 Sep. 2015 to include the IFD440 model and update the documentation.
XI. Amended on 10 Apr. 2017 to include additional models of the IFD and Software Release 10.2; to update the Masted Document List (MDL), the Aircraft Flight Manual Supplement (AFMS) and the Instructions for Continued Airworthiness (ICA); and to include items 115 through 123 on the ANAC Approved Model List (AML) for CST No. 2014S12-04, and update items 7, 12, 15, 17, 21, 23, 25, 29, 30, 34, 36, 39, 43, 61, 68, 80, 82, 85 and 91 on the ANAC Approved Model List (AML) for CST No. 2014S12-04.
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Documento assinado eletronicamente por MARIO IGAWA, Gerente-Geral de Certificação de Produtos Aeronáuticos, em 13/04/2017, às 16:30, conforme horário oficial de Brasília, com fundamento no art. 6º, § 1º, do Decreto nº 8.539, de 8 de outubro de 2015.
Documento assinado eletronicamente por ROBERTO JOSÉ SILVEIRA HONORATO, Superintendente de
AeronavegaRbEilLidEaAdSeE,DemFO1R3T/0H4E/2E0X1C7L,UàSsIV1E9:U3S6E, cBoYn:fHorOmNeEYhWorEáLriLoEoMfiPcLiaOlYdEeEBArMasEíRliIaC,AcSom fundamento no art. 6º, § 1º, do Decreto nº 8.539, de 8 de outubro de 2015.
A autenticidade deste documento pode ser conferida no site http://sistemas.anac.gov.br/sei/controlador_externo.php? acao=documento_conferir&id_orgao_acesso_externo=0, informando o código verificador 0563239 e o código CRC C19CE64D.
Referência: Processo nº 00066.506252/2017-30
SEI nº 0563239
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
ANAC LISTA DE MODELOS APROVADOS (LMA) PARA CST
(ANAC APPROVED MODEL LIST (AML) FOR (CST))
NÚMERO:
2014S12-04
(Number)
ITEM AIRCRAFT MAKE
1
Aeronautica Macchi S.p.A
2
Aviat Aircraft, Inc.
3
Aviat Aircraft, Inc.
Dynac
4 Aerospace
Corp.
5
Alexandria Aircraft
6
American Champion
7
American Champion
8 B-N Group LTD
9
Boeing
10
Textron Aviation
11
Textron Aviation
12
Textron Aviation
13
Textron Aviation
14
Textron Aviation
15
Textron Aviation
16
Textron Aviation
F-400-01-Anexo (AML)
AIRCRAFT MODEL(S)
AL60
A-1
S-2A
Aero Commander 100
14-19-3, 17-30
8KCAB, 8GCBC
7ECA, 7EC, 7GCB, 7GCAA, 7GCBC, 7KCAB
BN-2A-8, BN-2A-9, BN-2A-21, BN2A-27, BN-2B-21 AT-6D, T-6G 140A 120, 140
150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, A150L, 150M, 150K,
A150M, 152, A152
T-50
170, 170A, 170B 172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P,
172Q 172R, 172S
TYPE CERTIFICATE
NUMBER
CERTIFICATION BASIS
MODEL SPECIFIC INFORMATION
7A12 (FAA)
CAR 3
-
9801 (ANAC)
14 CFR Part 23
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements
A8SO (FAA) 14 CFR Part 23
-
1A21 (FAA)
CAR 3
-
1A3 (FAA)
A21CE (FAA)
A-759 (FAA) BA6
(CAA/UK) A-2-575 (FAA)
CAR 3
14 CFR Part 23
14 CFR Part 23 BCAR 3 CAR 4a
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements.
-
-
5A2 (FAA)
CAR 3
-
A-768 (FAA)
CAR 3
-
3A19 (FAA)
CAR 3 14 CFR Part 23
-
A-722 (FAA) A-799 (FAA)
CAR 4a CAR 3
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements
-
3A12 (FAA)
CAR 3 14 CFR Part 23
9705 (ANAC)
RBHA 23 14 CFR Part 23
Fl. 01 de 07
-
-
H.02-4438-0
UP793797
UP793797
ITEM 17 18 19 20
AIRCRAFT MAKE
Textron Aviation Textron Aviation Textron Aviation
Textron Aviation
21
Textron Aviation
22
Textron Aviation
23
Textron Aviation
24
Textron Aviation
25
Textron Aviation
26
Textron Aviation
27
Textron Aviation
28
Textron Aviation
29
Textron Aviation
30
Textron Aviation
31
Textron Aviation
32
Textron Aviation
33
Textron Aviation
34
Textron Aviation
35
Textron Aviation
36
Textron Aviation
37
Textron Aviation
F-400-01-Anexo (AML)
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
AIRCRAFT MODEL(S)
TYPE CERTIFICATE
NUMBER
CERTIFICATION BASIS
172RG, R172K, 175, 175A, 175B, 175C
3A17 (FAA)
CAR 3
MODEL SPECIFIC INFORMATION
-
177, 177A, 177B
A13CE (FAA) 14 CFR Part 23
-
177RG
A20CE (FAA) 14 CFR Part 23
-
180, 180A, 180B, 180C, 180D,
180E, 180F, 180G, 180H, 180J, 5A6 (FAA)
CAR 3
-
180K
182, 182A, 182B, 182C, 182D,
182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P,
3A13 (FAA)
CAR 3 14 CFR Part 23
-
182Q, 182R, R182 T182, TR182
182S, 182T, T182T
9706 (ANAC)
RBHA 23 14 CFR Part 23
-
185, 185A, 185B, 185C, 185D, 185E, A185E, A185F
3A24 (FAA)
CAR 3
-
190, 195
A-790 (FAA)
CAR 3
-
206, P206, P206A, P206B, P206C,
P206D, P206E, TP206A, TP206B,
TP206C, TP206D, TP206E, TU206A,
TU206B, TU206C, TU206D,
A4CE (FAA) 14 CFR Part 23
-
TU206E, TU206F, TU206G, U206, U206A, U206B, U206C, U206D,
U206E, U206F, U206G
206H, T206H
1999T06
RBHA 23
(ANAC) 14 CFR Part 23
-
207, 207A, T207, T207A
A16CE (FAA) 14 CFR Part 23
-
208, 208B
8805 (ANAC)
RBHA 23 14 CFR Part 23
-
210, 210A, 210B, 210C, 210D,
210E, 210F, 210G, 210H, 210J,
210K, 210L, 210M, 210N, 210R,
210-5 (205), 210-5A (205A), 210N, 3A21 (FAA)
CAR 3
-
P210R, T210F, T210G, T210H,
T210J, 210K, T210L, T210M,
T210N, T210R
310, 310A, 310B, 310C, 310D,
310F, 310G, 310H, 310I, 310J, 310K, 310L, 310N, 310P, 310Q,
3A10 (FAA)
CAR 3
-
310R, T310R
320A, 320C, 320E, 340, 340A 3A25 (FAA)
CAR 3
-
336
A2CE (FAA)
CAR 3
-
337A, 337C, 337D, 337G
A6CE (FAA)
CAR 3 14 CFR Part 23
-
401, 401A, 401B, 402, 402A, 402B,
402C, 411, 411A, 414, 414A, 421, A7CE (FAA)
CAR 3
-
421B, 421C
404
A25CE (FAA) 14 CFR Part 23
-
LC41-550FG, LC42-550FG, T240 501, 551
2007T01 (ANAC)
A27CE (FAA)
Fl. 02 de 07
RBAC 23 14 CFR Part 23 14 CFR Part 23
-
The aircraft's equipmanent list must be updated for single pilot operation.
H.02-4438-0
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
ITEM
AIRCRAFT MAKE
AIRCRAFT MODEL(S)
TYPE CERTIFICATE
NUMBER
CERTIFICATION BASIS
MODEL SPECIFIC INFORMATION
38
Textron Aviation
525, 525A
9304 (ANAC)
RBAC 23 14 CFR Part 23
The aircraft's equipmanent list must be updated for single pilot operation.
39
Cirrus
SR20, SR22, SR22T
2005T05 (ANAC)
RBAC 23 14 CFR Part 23
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements
40 CPAC Inc.
112, 114
A12SO (FAA)
CAR 3
-
41
Viking Air Limited
DHC-2 Mk I, DHC-2 Mk II, DHC-2 Mk III
A-806 (FAA)
CAR 3
-
Diamond
42
Aircraft
Industries
DA20-C1
2009T04 (ANAC)
RBHA 23 14 CFR Part 23
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements
Diamond
43
Aircraft
Industries
DA 40, DA 40F, DA 40NG
2008T04 (ANAC)
RBHA 23 14 CFR Part 23
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements.
44 Embraer
EMB-110P1, EMB-110P2
7202 (ANAC)
RBHA 23 14 CFR Part 23
-
45
Extra
EA300/L
2012T14 (ANAC)
RBHA 23 14 CFR Part 23
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements.
46
M7 Aerospace LLC
SA227-AT
2007T07 (ANAC)
RBHA 23 CAR 3
14 CFR Part 23
-
47
M7 Aerospace LLC
SA227-AC
2007T05
RBHA 23
(ANAC) 14 CFR Part 23
-
48
M7 Aerospace LLC
SA227-CC, SA227-DC
2007T06
RBHA 23
(ANAC) 14 CFR Part 23
-
Maule M-4, M-4-210C, M-6-235, M-7-235,
49 Aerospace M-7-235B, MT-7-235, MX-7-180, 3A23 (FAA)
Tecnology, Inc.
MX-7-235, MXT-7-180
CAR 3
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements.
50
Maule M-7-235C, MXT-7-160, MX-7-180A,
Aerospace MX-7-180B, MX-7-420, MXT-7-160,
Tecnology, Inc.
MXT-7-180A, M-8-235
9310 (ANAC)
RBHA 23 CAR 3
14 CFR Part 23
Wire Harness overbraid is required for IFR Installations. Reference the
Installation Manual for installation requirements.
Mitsubishi MU-2B, MU-2B-10, MU-2B-20, MU-
51
Heavy
2B-15, MU-2B-30, MU-2B-35, MU- A2PC (FAA)
CAR 3
-
Industries Ltd. 2B-25, MU-2B-26, MU-2B-36
Mitsubishi MU-2B-25, MU-2B-35, MU-2B-26,
52
Heavy
MU-2B-36, MU-2B-26A, MU-2B- A10SW (FAA)
CAR 3
-
Industries Ltd.
36A, MU-2B-40, MU-2B-60
53
Mooney Aircraft Corp.
M20A, M20B, M20C, M20E, M20F
2A3 (FAA)
CAR 3
-
54
Mooney Aircraft Corp.
M20J, M20K, M20M, M20R, M20TN
RBHA 23
8701 (ANAC)
CAR 3
14 CFR Part 23
-
55
Sierra Hotel Aero Inc.
Navion, Navion E, Navion G, Navion H
A-782 (FAA)
CAR 3
-
56
SOCATA
MS885, MS894 E
7A14 (FAA)
CAR 3
-
UP793797
57
Vulcanair S.p.A.
Piaggio Aero
58 Industries
S.p.A
F-400-01-Anexo (AML)
P68C, P68 "Observer 2" P-180
2008T10 (ANAC)
2010T08 (ANAC)
Fl. 03 de 07
RBAC 23 14 CFR Part 23
RBHA 23 RAI Parte 223 14 CFR Part 23
-
H.02-4438-0
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
ITEM
AIRCRAFT MAKE
59
Pilatus Aircraft Limited
60
Pilatus Aircraft Limited
61 GA8 Airvan
AIRCRAFT MODEL(S) PC-12, PC-12/45, PC-12/47
PC-6/B2-H4 GA8, GA8-TC320
TYPE CERTIFICATE
NUMBER
CERTIFICATION BASIS
9605 (ANAC)
RBHA 23 14 CFR Part 23
2011T04 (ANAC)
CAR 3
2014T05
RBAC 23
(ANAC) 14 CFR Part 23
62
FS2003 Corporation
PA-12
A-780 (FAA) 14 CFR Part 23
PA-28-140, PA-28-160, PA-28-150,
PA-28-151, PA-28-161, PA-28-180,
63
Piper Aircraft
PA-28-235, PA-28R-180, PA-28R200, PA-28-181, PA-28R-201, PA-
2A13 (FAA)
28R-201T, PA-28RT-201, PA-28-236,
PA-28RT-201T
PA-18, PA-18A, PA-18
64
Piper Aircraft
"105" (Special), PA-18 "135", PA18A "135", PA-18 "150", PA-18A
1A2 (FAA)
"150"
CAR 3 CAR 3
65 Piper Aircraft
PA-20 and PA-20 "135"
1A4 (FAA)
CAR 3
66
Piper Aircraft
PA-22, PA-22-108, PA-22-135, PA-22-150, PA-22-160
1A6 (FAA)
CAR 3
PA-32-260, PA-32-300, PA-32R-300,
PA-32RT-300, PA-32RT-300T, PA67 Piper Aircraft 32R-301(HP), PA-32R-301(SP), PA- A3SO (FAA)
CAR 3
32-301, PA-32R-301T, PA-32-301FT,
PA-32-301XTC
68
Piper Aircraft
PA-23, PA-23-160, PA-23-235, PA23-250
1A10 (FAA)
CAR 3
69 Piper Aircraft
PA-30, PA-39
A1EA (FAA)
CAR 3
70
Piper Aircraft
PA-31, PA-31-300, PA-31-325, PA31-350
A20SO (FAA)
CAR 3
71 Piper Aircraft PA-31P, PA-31T, PA-31T1, PA-31T2 A8EA (FAA)
CAR 3
72 Piper Aircraft
PA-24, PA-24-250, PA-24-260, PA-24-400
1A15 (FAA)
CAR 3
73 Piper Aircraft PA-34-200, PA-34-200T, PA-34-220T A7SO (FAA)
CAR 3
74 Piper Aircraft
PA-42, PA-42-720, PA-42-1000
9206 (ANAC)
RBHA 23 14 CFR Part 23
75 Piper Aircraft
PA-44-180
2013T06
RBHA 23
(ANAC) 14 CFR Part 23
76 Piper Aircraft
PA-38-112
8402 (ANAC)
RBHA 23 14 CFR Part 23
MODEL SPECIFIC INFORMATION
-
-
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements.
-
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements. Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements. Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements.
-
-
-
-
77 Piper Aircraft
78 ASI Aviation
79
Beechcraft Corporation
F-400-01-Anexo (AML)
PA-46-350P, PA-46R-350T, PA-46-500TP
F406
9501 (ANAC)
RBHA 23 14 CFR Part 23
2006T01
RBHA 23
(ANAC) 14 CFR Part 23
C23, 23, A24R, A23, B24R, A23-24 A1CE (FAA)
CAR 3
Fl. 04 de 07
-
H.02-4438-0
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
ITEM
AIRCRAFT MAKE
80
Beechcraft Corporation
81
Beechcraft Corporation
82
Beechcraft Corporation
83
Beechcraft Corporation
84
Beechcraft Corporation
85
Beechcraft Corporation
86
Beechcraft Corporation
87
Beechcraft Corporation
88
Beechcraft Corporation
89
Beechcraft Corporation
90
Beechcraft Corporation
91
Beechcraft Corporation
92
Beechcraft Corporation
93
Beechcraft Corporation
94 Helio Aircraft
AIRCRAFT MODEL(S)
TYPE CERTIFICATE
NUMBER
CERTIFICATION BASIS
H35, J35, K35, M35, 35-33, N35, 35-
A33, 35-B33, P35, S35, 35-C33, V35,
V35A, V35B, 35-C33A, E33A, E33C, 3A15 (FAA)
CAR 3
36, A36, G36, F33A, F33C, G33,
A36TC, B36TC
35, A35, B35, C35, D35, E35, F35, G35
A-777 (FAA)
CAR 3
95, B95, 95-55, 95-A55, B95A, 95-
B55, 95-C55
3A16 (FAA)
CAR 3
D55, E55, 56TC, A56TC, 58, G58
58P, 58TC
A23CE (FAA) 14 CFR Part 23
D50, D50A, D50B, J50 200, 200T, A200, B200, B200T,
B200GT, B200CGT 300, B300, B300C
99, C99, 100, A100, A100A, B100
5A4 (FAA)
CAR 3
A24CE (FAA) 14 CFR Part 23
9008 (ANAC)
RBHA 23 14 CFR Part 23
A14CE (FAA) 14 CFR Part 23
F90
A31CE (FAA) 14 CFR Part 23
60, A60, B60
A12CE (FAA) 14 CFR Part 23
D17S
A-649 (FAA) 14 CFR Part 23
65, A65, 65-80, 65-A80, 65-B80, 6588, 65-90, 65-A90, 70, B90, C90, C90A, C90GT, G90GTi, E90
3NM, D18S, E18S, G18S, H18, C45H, TC-45H
3A20 (FAA)
CAR 3 14 CFR Part 23
A-765 (FAA)
CAR 3
390
2001T07
RBHA 23
(ANAC) 14 CFR Part 23
H-295, HT-295, H-391B
1A8 (FAA)
CAR 3
MODEL SPECIFIC INFORMATION
-
-
-
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements. -
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements. -
95
Howard
Lockheed
96
Martin Aeronautics
Co.
97 REVO Inc.
98 REVO Inc.
99
SOCATA
100 SOCATA
F-400-01-Anexo (AML)
DGA-15P
18 Lake LA-4, Lake LA-4A,
Lake LA-4-200 Lake Model 250 TB 9, TB 10, TB 20, TB 21 TBM 700 (TBM 850)
A-717 (FAA)
CAR 4a
A-723 (FAA) CAR 4a
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements.
-
1A13 (FAA)
CAR 3
CAR 3
8704 (ANAC) RBHA 23
14 CFR Part 23
9211 (ANAC)
RBHA 23 14 CFR Part 23
9307 (ANAC)
RBHA 23 14 CFR Part 23
Fl. 05 de 07
-
-
-
H.02-4438-0
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
ITEM
AIRCRAFT MAKE
AIRCRAFT MODEL(S)
TYPE CERTIFICATE
NUMBER
CERTIFICATION BASIS
MODEL SPECIFIC INFORMATION
Sky
101 Enterprices
RC-3
A-769 (FAA)
CAR 3
-
Inc.
Short Brothers
102
&
Harland Ltd.
SC-7 Series 3
A15EU (FAA)
14 CFR Part 23
-
103
True Flight Holdings
AA-1
A11EA (FAA)
14 CFR Part 23
-
104
True Flight Holdings
AA-5
A16EA (FAA)
14 CFR Part 23
-
105
Twin Commander
500, 500-B, 500-U, 500-S, 520, 560, 560-E
6A1 (FAA)
CAR 3
-
106
Twin Commander
560-F, 680E, 680F, 680FL, 680V, 680W, 681, 690, 690A, 690B, 690C,
690D, 695, 695A
2A4 (FAA)
CAR 3
-
Univair 107 Aircraft
Corporation
108, 108-1, 108-2, 108-3
A-767 (FAA)
CAR 3
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements.
Indústria
108 Aeronáutica
EMB-710D
7503 (ANAC) CAR 3
-
Neiva
109
Indústria Aeronáutica
Neiva
EMB-711B, EMB-711C, EMB-711ST, EMB-711T
7502 (ANAC)
CAR 3
-
Indústria
110 Aeronáutica
EMB-712
7801 (ANAC) CAR 3
-
Neiva
Indústria
111 Aeronáutica
EMB-720C, EMB-720D
7504 (ANAC) CAR 3
-
Neiva
Indústria
112 Aeronáutica
EMB-721C, EMB-721D
7506 (ANAC) CAR 3
-
Neiva
Indústria 113 Aeronáutica
Neiva
EMB-810C, EMB-810D
7501 (ANAC)
RBAC 23 14 FR Part 23
-
Indústria
114 Aeronáutica
EMB-820C
7505 (ANAC) CAR 3
-
Neiva
115
Air Tractor Inc.
AT-401, 401B, AT-402A, AT-402B, AT-
RBAC 23
501, AT-502, AT-502B, AT-503A, AT- 8801 (ANAC) 14 FR Part 23
504
-
Air Tractor
116
Inc.
AT-602, AT-802, AT-802A
2001T03 (ANAC)
RBHA 23 14 CFR Part
23
-
117
Alexandria Aircraft
17-30A
A18CE (FAA)
14 CFR Part 23
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements.
118
BrittenNorman
BN2A Mark III
BA8 (CAA/UK)
BCAR 3
-
Diamond 119 Aircraft
Industries
DA 42NG, DA 42M-NG
2010T03 (ANAC)
RBHA 23 14 CFR Part
23
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements.
UP793797
120
Pacific Aerospace
F-400-01-Anexo (AML)
750XL
2015T03 (ANAC)
Fl. 06 de 07
RBAC 23 14 FR Part 23
-
H.02-4438-0
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
ITEM
AIRCRAFT MAKE
121 Reims Aviation
122
Viking Air Limited
123
The Waco Aircraft, Co.
AIRCRAFT MODEL(S) FR182
DHC-6 Series 400
YMF
TYPE CERTIFICATE
NUMBER
CERTIFICATION BASIS
A42EU (FAA)
CAR 3
2016T07
RBHA 23
(ANAC) 14 CFR Part 23
2016T05 (ANAC)
Aero 7A
MODEL SPECIFIC INFORMATION
-
-
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation
requirements.
Aprovação ANAC:
(ANAC Approval:)
MÁRIO IGAWA Gerente-Geral, Certificação de Produto Aeronáutico
(General Manager, Aeronautical Product Certification)
Data da aprovação ANAC: 11 Apr. 2017
(ANAC Approval Date:)
Revisão:
02
(Rev.:)
F-400-01-Anexo (AML)
Fl. 07 de 07
H.02-4438-0
Documento assinado eletronicamente por MARIO IGAWA, Gerente-Geral de Certificação de Produtos Aeronáuticos, em 12/04/2017, às 09:24, conforme horário oficial de Brasília, com fundamento no art. 6º, § 1º, do Decreto nº 8.539, de 8 de outubro de 2015.
A autenticidade deste documento pode ser conferida no site http://sistemas.anac.gov.br/sei/controlador_externo.php? acao=documento_conferir&id_orgao_acesso_externo=0, informando o código verificador 0563323 e o código CRC 10FB83DD.
Referência: Processo nº 00066.506252/2017-30
SEI nº 0563323
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
*itrfrEh/lhis Cotifua* is isswd n
Avidyne Corporation
4 Middlesex Green, Suite 221,561 Virginia Road, Concord, MA0l742
fiH,3trffif#;,rr,"
configuration or of a dual configuration Avidyne corporation Integrated Flight Display, Model IFD 5xx
and/or Model IFD 4XX, loaded with Release 10.2 software (or later FAA approved release), in accordance with Avidyne Corporation Master Document List (MDL), Document Nurnber AVIFD-306, Revision I I , dated February 28,2017 ,or later FAA approved revision.
Apploved Chinese Placards and Markings: N/A.
rAuur4rt'u Thi; k n cmifi ilwr dcsigz. clwrye of obow ciatil urorwutbal pro&n nwetr opplicdln Chirw Cioil Aoiotbn fugula-
tiow.Cioil-fuiotbn Ailministrotian of Chino wlidares tha $qplemennl Typc Certifieata /V'o.
issud
Xu Chaoqun Director General
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX GPS/Nav/Comm
Approved Model List for STC SA00343BO
AVIDYNE
CORPORATION
4 Middlesex Green, Suite 221 561 Virginia Road Concord MA 01742
NICHOLA Digitally signed by NICHOLAS REDIESS
S REDIESS Date: 2019.06.11 10:48:35 -04'00'
FAA Approved: ______________________ IRU Manager Boston Aircraft Certification Office Federal Aviation Administration Burlington, MA
Document Number
AVIFD-318
Control Category
Revision
Description
ECO
00
Initial Release
ECO-14-200
01
Added 700-00179-XXX
ECO-15-129
02
Updated Table
ECO-16-185
03
Updates for 10.2
ECO-16-326
04
Fixed tables, added Quest Kodiak, Dornier 228, top cub CC19, Extra EA300LC
ECO-18-067
05
Added Ruschmeyer R90-230RG
ECO-19-035
06
Add Swift Museum Globe GC-1A, GC-1B
ECO-19-111
N/A Date 07/11/14 03/20/15 06/02/16 12/21/16
04/10/18
02/14/19 05/09/19
Confidential property of Avidyne Corporation Not to be disclosed without permission
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Table of Contents
1. Introduction............................................................................. 3 2. Approved Model List.............................................................. 4
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 2 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
1. Introduction
This document is the FAA Approved Model List for STC SA00343BO for the installation of the Avidyne 700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX GPS/Nav/Comm into eligible aircraft. Revisions to the AML must be coordinated through the STC holder, and require FAA approval.
IMPORTANT NOTICE
This STC is only applicable to the 14 CFR Part 23 aircraft which are listed in this AML. Installations in 14 CFR Part 25, Part 27 and Part 29 aircraft are not authorized under this STC.
IMPORTANT NOTICE
With respect to the AML STC, the physical mounting of the antenna is specifically excluded from the approval in the case of installations on the pressure vessel of pressurized aircraft, composite aircraft, and aircraft with a certification basis of Amendment 23-45 or later, unless approved data is listed in the Master Document List of the STC.
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 3 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
2. Approved Model List
Aircraft Make Aermacchi S.p.A.
Aircraft Model(s)
F.260, F.260B, F.260C, F.260D, F.260E, F.260F
Type Certificate Number
A10EU
Certification Basis
CAR 3
S.211A
A86EU 14 CFR Part 23
Model Specific Information
Aeronautica Macchi S.p.A
S.205-18/F, S.205-18/R, S.20520/F, S.205-20/R, S.205-22/R, S.208, S.208A
AL 60, AL 60-B, AL 60-F5, AL 60C5
A9EU 7A12
14 CFR Part 23 CAR 3
Aeronautica Macchi S.p.A. & AerferIndustrie S.p.A.
Aerostar Aircraft Corporation
AM-3
PA-60-600 (Aerostar 600), PA-60601 (Aerostar 601), PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P), PA-60-700P (Aerostar 700P)
A19EU A17WE
14 CFR Part 23 14 CFR Part 23
360, 400
A11WE 14 CFR Part 23
Air Tractor Inc.
Alexandria Aircraft, LLC
(Bellanca)
AT-250, AT-300, AT-301, AT302, AT-400, AT-400A AT-401, AT-401A, AT-401B, AT402, AT-402A, AT-402B, AT501, AT-502, AT-502A, AT502B, AT-503, AT-503A, AT-504 AT-602, AT-802, AT-802A 14-19, 14-19-2, 14-19-3, 14-193A, 17-30, 17-31, 17-31TC
17-30A, 17-31A, 17-31ATC
A9SW A17SW
A19SW 1A3
A18CE
14 CFR Part 23 14 CFR Part 23
14 CFR Part 23 CAR 3
14 CFR Part 23
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 4 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make American Champion
Aircraft Corp.
Atlantic Coast Seaplanes, LLC
Aircraft Model(s) 8KCAB, 8GCBC
Type Certificate Number
A21CE
7ECA, 7EC, 7FC, 7GC, 7GCA, 7GCB, 7GCBA, 7GCAA, 7GCBC, 7HC, 7JC, 7KCAB, 7KC
A-759
402
A3CE
G-21C, G-21D, G-21E, G-21G
4A24
Certification Basis
14 CFR Part 23
14 CFR Part 23
CAR 3
CAR 3
Model Specific Information
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Aviat Aircraft, Inc.
A-1, A-1A, A-1B, A-1C-180, A1C-200
S-1S, S-1T, S-2, S-2A, S-2S, S2B, S-2C
B-N Group Ltd. (Britten-Norman)
Textron Aviation Inc. (Beechcraft)
BN2, BN2A, BN2A-2, BN2A-3, BN2A-6, BN2A-8, BN2A-20, BN2A-21, BN2A-26, BN2A-27, BN2B-20, BN2B-21, BN2B-26, BN2B-27, BN2T, BN2T-4R, BN2A-9
BN.2A MK III, BN.2A MK III-2, BN.2A MK III-3
18A, S18A
G17S
A22NM A8SO A17EU
14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
A29EU 14 CFR Part 23
TC 630
Aero 7A
TC 779
Aero 7A CAR 4
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 5 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
Textron Aviation Inc. D17S (Army UC-43, UC-43B,
(Beechcraft)
Navy GB-1, GB-2), SD17S
18D, A18A, A18D, S18D, SA18A, SA18D
Type Certificate Number
A-649
A-684
Certification Basis
14 CFR Part 23
Aero 7A
Model Specific Information
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
3N, 3NM, 3TM, JRB-6, D18C, D18S, E18S, RC-45J (SNB-5P), E18S-9700, G18S, H18, C-45G, TC-45G, C-45H, TC-45H, TC45J, UC-45J (SNB-5)
35, A35, B35, C35, D35, E35, F35, G35, 35R
H35, J35, K35, M35, 35-33, N35, 35-A33, 35-B33, P35, S35, 35C33, E33, F33, V35, V35A, V35B, 35-C33A, E33A, E33C, 36, A36, G36, F33A, F33C, G33, A36TC, B36TC, G36
95, B95, 95-55, 95-A55, B95A, D95A, E95, 95-B55, 95-B55A, 95-B55B, 95-C55, D55, 95C55A, D55A, E55, E55A, 56TC, A56TC, 58, 58A, G58
65, 65-A90-1, A65, 65-A90-2, A65-8200, 65-A90-3, 65-80, 65A90-4, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, 70, B90, C90, C90A, C90GT, C90GTi, E90, H90,
45 (YT-34), A45 (T-34A) or (B45), D45 (T-34B)
50 (L-23A), B50 (L-23B), C50, D50 (L-23E), D50A, D50B, D50C, D50E, D50E-5990, E50 (L-23D, RL-23D), F50, G50, H50, J50
19A, B23, B19, C23, M19A, A24, 23, A24R, A23, B24R, A23A, C24R, A23-19, A23-24
60, A60, B60
A-765 A-777 3A15
3A16 3A20
5A3 5A4 A1CE A12CE
CAR3
CAR 3 CAR 3
CAR 3
CAR3, 14 CFR Part 23
CAR 3 CAR 3
CAR 3 14 CFR Part 23
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 6 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Textron Aviation Inc. (Beechcraft)
Aircraft Model(s)
99, 99A, 99A(FACH), A99, A99A, B99, C99, 100, A100 (U21F), A100A, A100C, B100 58P, 58PA, 58TC, 58TCA
Type Certificate Number
Certification Basis
A14CE 14 CFR Part 23
A23CE 14 CFR Part 23
Model Specific Information
Bellanca Aircraft Corporation
Bernd Hager/Anatoli Strobbe GbR (Ruschmeyer Luftfahrttechnik GmbH) The Boeing Company
200, A100-1 (U-21J), 200C, 200CT, 200T, A200 (C-12A) or (C-12C), A200C (UC-12B), A200CT (C-12D) or (FWC-12D) or (RC-12D) or (C-12F) or (RC12G) or (RC-12H) or (RC-12K) or (RC-12P), or (RC-12Q), B200, B200C (C-12F) or (UC-12F) or (UC-12M), or (C-12R), B200CT, B200T, 300, B300, B300C, 300LW, 1900, 1900C (C-12J), 1900D, B200GT, B200CGT T-34C (T-34C-1) (34C) 76 77 F90 2000 3000 390DD
14-13, 14-13-2, 14-13-3, 14-133W
R90-230RG
A24CE
A26CE A29CE A30CE A31CE A38CE A00009WI A00010WI
A-773
A77EU
14 CFR Part 23
14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
CAR 4a
14 CFR Part 23
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
BC-1A, AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), SNJ-7, T-6G
NA-260
A-2-575 1A18
CAR 4a CAR 3
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 7 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
Bushmaster Aircraft Corporation
Cirrus Design Corporation
Bushmaster 2000
SR20, SR22, SR22T SF50
Commander Aircraft 112, 114, 112TC, 112B,
Corporation
112TCA, 114A, 114B, 114TC
Type Certificate Number
A19WE
Certification Basis
CAR 3
Model Specific Information
A00009CH A00018CH
A12SO
14 CFR Part 23 14 CFR Part 23
CAR 3
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Cub Crafters, Inc. CC19-180
Top Cub Aircraft, Inc. CC18-180, CC18-180A
Diamond Aircraft Industries Inc.
(Canada)
DA 20-A1, DA 20-C1
Diamond Aircraft Industries GmbH
(Austria)
DA 40, DA 40 F, DA 40 NG
DA 42, DA 42 NG, DA 42 M-NG, DA 62
Discovery Aviation, XL-2 Inc.
(Liberty)
Dynac Aerospace Corp.
(Aero Commander)
Volaire 10, Volaire 10A, Aero Commander 100, Aero Commander 100A, Aero Commander 100-180
A00053SE A00006SE
TA4CH A47CE A57CE A00008DE 1A21
14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
CAR 3
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 8 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
EADS-PZL "Warazawa-Okecie"
S.A.
Embraer S.A.
Aircraft Model(s)
PZL-104 WILGA 80, PZL-104M WILGA 2000, PZL-104MA WILGA 2000 PZL-KOLIBER 150A, PZLKOLIBER 160A EMB-110P1, EMB-110P2
Type Certificate Number
Certification Basis
A55EU 14 CFR Part 23
A69EU 14 CFR Part 23 A21SO 14 CFR Part 23
Model Specific Information
Extra Flugzeuproduktions-
und Vertriebs
FS2003 Corporation (Piper Super Cruiser)
Found Aircraft Canada, Inc. Found Brothers Aviation Limited Fuji Heavy Ind. GA 8 Airvan (Pty) Ltd GROB Aircraft AG
Grumman American Aviation Corporation
EA 400, EA 400-500
EA 300, EA 300/L, EA 300/S, EA 300/200, EA 300/LC
PA-12, PA-12S
FBA-2C, FBA-2C1, FBA-2C2, FBA-2C3, FBA-2C4, FBA-2C3T, FBA-2C4T FBA Centennial "100"
A43CE A67EU A-780 A7EA A13EA
14 CFR Part 23
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
14 CFR Part 23
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
14 CFR Part 23
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
CAR 3
14 CFR Part 23
14 CFR Part 23
FA-200-160, FA-200-180, FA200-180AO GA8, GA8-TC 320
G520, G520T
G109, G109B
G120A
G120TP-A
G115, G115A, G115B, G115C, G115C2, G115D, G115D2, G115EG Grumman G-21, Grumman G21A
A4PC
CAR 3
A00011LA A63EU G43EU A49CE
A00067CE A57EU
CAR 3 14 CFR Part 23
FAR 21 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
TC 654
Aero 7a
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 9 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
Type Certificate Number
Certification Basis
Model Specific Information
Gulfstream American G-44, G-44A, SCAN Type 30 Corporation
A-734
CAR 4a
Helio Aircraft, LLC H-250, H295, HT-295, H391,
1A8
(Taylorcraft)
H391B, H-395, H395A, H-700,
H-800
15A, 20
3A3
CAR 3
CAR 4a
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
500 HST-550, HST-550A
A2EA A4EA
CAR 3 CAR 3
Howard Aircraft Foundation
DGA-15P (Army UC-70; Navy GH-1, GH-2, GH-3, NH-1), DGA15J (Army UC-70B), DHA-15W
A-717
CAR 4a
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Industrie
P.166, P.166B, P.166C, P.166
7A4
Aeronautiche e
DL3
Meccaniche
(Piaggio)
CAR 3 FAR 21 FAR 23
Interceptor Aviation 200, 200A, 200B, 200C, 200D,
3A18
Inc. (Meyers)
400
CAR 3
JGS Properties, LLC 11A, 11E (Luscombe)
A-804
CAR 3
King's Engineering Fellowship, The
(TKEF)
4500-300, 4500-300 Series II Model 44 (Angel)
A17CE A2WI
14 CFR Part 23 14 CFR Part 23
Learjet Inc.
23
A5CE
CAR3
Lockheed Martin Aeronautics Company
402-2 18
2A11 A-723
CAR 3 CAR 4a
Lockheed Aircraft Corporation
12-A (Army UC-40, UC-40A; Navy JO-1, JO-2)
TC 616
Aero 7a
M7 Aerospace LLC (Fairchild)
SA26-T, SA26-AT, SA226-T, SA226-AT, SA226-T(B), SA227AT, SA227-TT
SA-226-TC, SA227-AC (C-26A), SA227-BC (C-26A), SA227-PC
SA227-CC, SA227-DC (C-26B)
A5SW
A8SW A18SW
CAR3
14 CFR Part 23 14 CFR Part 23
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 10 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make Maule Aerospace Technology, Inc.
MICCO Aircraft Company Inc. Mitsubishi Heavy Industries, Ltd.
Mooney International Corp.
Pacific Aerospace Limited
Piaggio Aero Industries S.p.A.
Aircraft Model(s)
Type Certificate Number
Certification Basis
Bee Dee M-4, M-4, M-4C, M-4S, 3A23 M-4T, M-4-180C, M-4-180S, M4-180T, M-4-180V, M-4-210, M4-210C, M-4-210S, M-4-210T, M-4-220, M-4-220C, M-4-220S, M-4-220T, M-5-180C, M-5-200, M-5-210C, M-5-210TC, M-5220C, M-5-235C, M-6-180, M-6235, M-7-235, M-7-235A, M-7235B, M-7-235C, M-7-260, M-7260C, M-7-420, M-7-420A, M-7420AC, MT-7-235, MT-7-420, MX-7-160, MX-7-160C, MX-7180, MX-7-180A, MX-7-180B, MX-180C, MX-7-180AC, MX-7235, MX-7-420, MXT-7-160, MXT-7-180, MXT-7-180A, M-8235
CAR 3
MAC-125C, MAC-145, MAC145A, MAC-145B
3A1
CAR 4a
14 CFR Part 23
MU-2B, MU-2B-10, MU-2B-20, MU-2B-15, MU-2B-30, MU-2B35, MU-2B-25, MU-2B-36, MU2B-26
MU-2B-25, MU-2B-35, MU-2B26, MU-2B-36, MU-2B-26A, MU2B-36A, MU-2B-40, MU-2B-60
M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, M20R, M20S, M20TN, M20U, M20V
M22
A2PC A10SW
2A3
A6SW
CAR 3 CAR 3 CAR 3
CAR 3
750XL
A50CE 14 CFR Part 23
Piaggio P-180
A59EU 14 CFR Part 23
Model Specific Information
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Pilatus Aircraft Limited
PC-12, PC-12/45, PC-12/47, PC12/47E
PC-7
A78EU A50EU
14 CFR Part 23 14 CFR Part 23
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 11 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Pilatus Aircraft Limited
Aircraft Model(s)
Type Certificate Number
PC-6, PC-6-H1, PC-6-H2, PC-
7A15
6/350, PC-6/350-H1, PC-6/350-
H2, PC-6/A, PC-6/A-H1, PC-6/A-
H2, PC-6/B-H2, PC-6/B1-H2,
PC-6/B2-H2, PC-6/B2-H4, PC-
6/C-H2, PC-6/C1-H2
Certification Basis
CAR3
Model Specific Information
Piper Aircraft
PA-18, PA-18S, PA-18 "105" (Special), PA-18S "105" (Special), PA-18A, PA-18 "125", PA-18S "125", PA-18AS "125", PA-18 "135", PA-18A "135", PA18S "135", PA-18AS "135", PA18 "150", PA-18A "150", PA18S "150", PA-18AS "150", PA-19, PA-19S
PA-20, PA-20S, PA-20 "115", PA-20S "115", PA-20 "135", PA20S "135"
PA-22, PA-22-108, PA-22-135, PA-22S-135, PA-22-150, PA22S-150, PA-22-160, PA-22S160
PA-23, PA-23-160, PA-23-250 (Navy UO-1), PA-23-235, PAE23-250, PA-23-250
PA-24, PA-24-250, PA-24-260, PA-24-400
PA-28-140, PA-28-160, PA-28150, PA-28-151, PA-28-161, PA28-180, PA-28S-160, PA-28S180, PA-28-235, PA-28R-180, PA-28R-200, PA-28-181, PA28R-201, PA-28R-201T, PA28RT-201, PA-28-201T, PA-28236, PA-28RT-201T
PA-30, PA-39, PA-40
1A2
1A4 1A6 1A10 1A15 2A13
A1EA
CAR 3
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
CAR 3 CAR 3
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
CAR 3
CAR 3 CAR 3
CAR 3
PA-32-260, PA-32-300, PA-32S300, PA-32R-300, PA-32RT-300, PA-32RT-300T, PA-32R-301 (HP), PA-32R-301 (SP), PA-32301, PA-32R-301T, PA-32301FT, PA-32-301XTC, PA-32301T
A3SO
CAR 3
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 12 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make Piper Aircraft
Aircraft Model(s)
PA-34-200, PA-34-200T, PA-34220T
Type Certificate Number
A7SO
Certification Basis
CAR 3
Model Specific Information
Polskie Zaklady Lotnicze Spolka zo.o. Quest Aircraft Design
LLC Reims Aviation S.A.
(Cessna)
REVO, Inc. (Lake)
PA-31P, PA-31T, PA-31T1, PA31T2, PA-31T3, PA-31P-350
PA-38-112
A8EA A18SO
PA-44-180, PA-44-180T
A19SO
PA-31, PA-31-300, PA-31-325, PA-31-350
PA-42, PA-42-720, PA-42-1000
A20SO A23SO
PA-46-310P, PA-46-350P, PA46R-350T, PA-46-500TP
PA-42-720R
A25SO A32SO
PZL M18, PZL M18A, PZL M18B A47EU
PZL M26 01
A44CE
PZL M28 05
A56CE
Kodiak 100
A00007SE
F150F, F150G, F150H, F150J, F150K, F150L, F150M, F152, FA150K, FA150L, FA150M, FA152, FRA150L, FRA150M
F172D, F172E, F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P, FP172D
FR172E, FR172F, FR172G, FR172G, FR172H, FR172J, FR172K
F182P, F182Q, FR182
A13EU A4EU A18CE A42EU
F177RG
F337E, FT337E, F337F, FT337F, F337G, FT337GP, F337H, FT337HP
F406
A26EU A23EU
A54EU
Colonial C-1, Colonial C-2, Lake 1A13 LA-4, Lake LA-4A, Lake LA-4P, Lake LA-4-200, Lake Model 250
CAR3
14 CFR Part 23 14 CFR Part 23
CAR3
14 CFR Part 23 14 CFR Part 23
14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
CAR 3 FAR 21
CAR 3 FAR 21 CAR 3 FAR 21 CAR 3 14 CFR Part 23 14 CFR Part 23 CAR 3 FAR 21 CAR 3 FAR 21 CAR 3, 14 CFR Part 23
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 13 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Robert E. Rust Jr. (de Havilland)
RUAG Aerospace Services GmbH
(Dornier)
Short Brothers & Harland Ltd.
Sierra Hotel Aero, Inc.
(Navion) Sky Enterprises, Inc.
(Republic) Slingsby Aviation Ltd.
SOCATA (Morane Saulnier)
SOCATA
SOCATA, S.A. (Grummond) SOCATA - Groupe AEROSPATIAL (Morane Saulnier) Legend Aviation and Marine LLC (STOL
Aircraft) Swift Museum Foundation (Globe)
Aircraft Model(s)
Type Certificate Number
DHC-1 Chipmunk, Mk 21, Mk 22, A44EU Mk 22A
Do 27 Q-6
Do 28 D, Do 28 D-1, Dornier 228-100, Dornier 228-101, Dornier 228-200, Dornier 228201, Dornier 228-202, Dornier 228-212
SC-7 Series 2, SC-7 Series 3
A8IN A16EU
A15EU
Navion (L-17A), Navion A (L17B) or (L-17C), Navion B, Navion D, Navion E, Navion F, Navion G, Navion H
RC-3
A-782 A-769
T67M260, T67M260-T3A
A73EU
Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235E, Rallye 235C, MS 880B, MS 885, MS 894A, MS 893A, MS 892A-150, MS 892E-150, MS 893E, MS 894E
TB 20, TB 10, TB 21, TB 9, TB 200
TBM 700A, TBM700B, TBM700C1, TBM700C2, TBM700N
GA-7 (Cougar)
7A14
A51EU A60EU A17SO
M.S. 760, M.S. 760 A, M.S. 760
7A3
B
UC-1
A6EA
GC-1A, GC-1B
A-766
Certification Basis
CAR 3 14 CFR Part 23
14 CFR Part 23 CAR 3
CAR 3 14 CFR Part 23
CAR 3
14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
CAR 3 14 CFR Part 23
Model Specific Information
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
See note 14 on the TCDS for all the models
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 14 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make Symphony Aircraft
Industries Inc.
Textron Aviation Inc. (Cessna)
Aircraft Model(s) OMF-100-160, SA 160
Type Certificate Number
A46CE
T-50 (Army AT-17, UC-78 series, and Navy JRC-1)
A-722
120, 140
190
195, 195A, 195B
170, 170A, 170B
310, 310A (USAF U-3A), 310B, 310C, 310D, 310E (USAF U-3B), 310F, 310G, 310H, 310I, 310J, 310J-1, 310K, 310L, 310N, 310P, E310H, E310J, T310P, 310Q, T310Q, 310R, T310R
172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172Q, 172R, 172S,
182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, 182S, 182T, R182, T182, T182T, TR182
172RG, P172D, R172E, R172F, R172G, R172H, R172J, R172K
175, 175A, 175B, 175C
150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, A150L, 150M, A150K, A150M, 152, A152
210, 210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L, 210M, 210N, 210R, 210-5 (205), 210-5A (205A), P210N, P210R, T210F, T210G, T210H, T210J, T210K, T210L, T210M, T210N, T210R
185, 185A, 185B, 185C, 185D, 185E, A185E, A185F
A-768 A-790 A-799 3A10
3A12 3A13
3A17 3A19 3A21
3A24
Certification Basis
14 CFR Part 23
CAR 4a
CAR 3 CAR 3 CAR 3 CAR 3
CAR 3, 14 CFR Part 23
CAR 3, 14 CFR Part 23
CAR 3 CAR 3 14 CFR Part 23 CAR 3
CAR 3
Model Specific Information
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 15 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Textron Aviation Inc. (Cessna)
Aircraft Model(s)
320, 320-1, 320A, 320B, 320C, 320D, 320E, 320F 340, 340A, 335 140A
180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K 525, 525A, 525B, 525C
336
206, 206H, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, T206H, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G
Type Certificate Number
3A25
Certification Basis
CAR 3
Model Specific Information
5A2
CAR 3
5A6
CAR 3
A1WI
A2CE A4CE
14 CFR Part 23
CAR 3 CAR 3, 14 CFR Part 23
The aircraft's equipment list must be updated for single
pilot operation.
337, 337A (USAF O2B), 337B, 337C, 337D, 337E, 337F, 337G, 337H, M337B (USAF O2A), P337H, T337B, T337C, T337D, T337E, T337F, T337G, T337H, T337H-SP 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425 188, 188A, 188B, A188, A188B, T188C 177, 177A, 177B
207, 207A, T207, T207A
177RG
404, 406
501, 551
441
T303
A6CE
A7CE
A9CE A13CE A16CE A20CE A25CE A27CE
A28CE A34CE
CAR 3, 14 CFR Part 23
CAR3
14 CFR Part 23
14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
14 CFR Part 23 14 CFR Part 23
The aircraft's equipment list must be updated for single
pilot operation
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 16 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Textron Aviation Inc. (Cessna)
Triton Aerospace LLC
(Adam Aircraft)
True Flight Holdings LLC
(American General)
Twin Commander Aircraft LLC
Univair Aircraft Corporation (Stinson)
Viking Air Limited (de Havilland)
Vulcanair S.p.A. (Partenavia)
The Waco Aircraft Company
Aircraft Model(s)
208, 208B LC40-550FG, LC41-550FG, LC42-550FG A500
AA-1, AA-1A, AA-1B, AA-1C
AA-5, AA-5A, AA-5B, AG-5B 500, 500A, 500B, 500U, 500S, 520, 560, 560A, 560E 560-F, 680, 680E, 680F, 680F(P), 680FL, 680FL(P), 680T, 680V, 680W, 681, 685, 690, 690A, 690B, 690C, 690D, 695, 695A, 695B, 720 700 108, 108-1, 108-2, 108-3, 108-5
DHC-2 Mk. I, DHC-2 Mk. II, DHC-2 Mk. III DHC-3 DHC-6-1, DHC-6-100, DHC-6200, DHC-6-300 DHC-6-400 P.68, P.68B, P.68C, P.68C-TC, P.68 Observer, P.68 "Observer 2", P.68-TC "Observer", AP68TP-300 "Spartacus", AP68TP-600 "Viator", P.68R SF600, SF600A 2T-1A, 2T-1A-1, 2T-1A-2 YMF
Type Certificate Number
Certification Basis
A37CE 14 CFR Part 23
A00003SE 14 CFR Part 23
A00009DE 14 CFR Part 23
A11EA 14 CFR Part 23
A16EA 6A1
14 CFR Part 23 CAR 3
2A4
CAR 3
A12SW A-767
14 CFR Part 23 CAR 3
A-806
CAR 3
A-815 A9EA
CAR 3 CAR3
A31EU 14 CFR Part 23
A61EU A18EA ATC 542
14 CFR Part 23 Aero 7A Aero 7A
Model Specific Information
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
Wire Harness overbraid is required for IFR
installations. Reference the Installation Manual for
installation requirements.
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 17 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX
Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
WSK PZL MIELEC and OBR SK MIELEC
Zenair Ltd.
Zlin Aircraft A.S.
PZL M20 03
CH2000 Z-242L, Z-143L ZLIN 526L
Type Certificate Number
Certification Basis
A68EU 14 CFR Part 23
Model Specific Information
TA5CH A76EU A30EU
14 CFR Part 23 14 CFR Part 23 14 CFR Part 23
FAA Approved Date: _______________
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 18 of 18
AVIFD-318 Revision: 06, Date: 05/09/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne 700-00182-XXX and 700-00179-XXX GPS/Nav/Comm
EASA Approved Model List for STC SA00343BO
AVIDYNE
CORPORATION
4 Middlesex Green - Suite 221
561 Virginia Road Concord MA 01742
)$$DSSURYHG RQWKHEHKDOIRI EASA
NICHOLAS Digitally signed by NICHOLAS REDIESS
REDIESS Date: 2019.02.21 08:49:43 -05'00'
Approved: ______________________
Document Number
AVIFD-485
Control Category
Revision
Description
ECO
00
Initial Release
ECO-16-123
01
Harmonized with 8 Apr 2016 EASA Aircraft List
ECO-16-138
02
Add Textron 177RG, Quest, Slingsby, Short Bros, Quest,
ECO-18-067
03
Added Ruschmeyer R90-230RG
ECO-19-035
N/A Date 04/13/16 05/02/16 04/11/18 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Table of Contents
1. Introduction............................................................................. 3 2. Approved Model List.............................................................. 4
EASA Approved Date: ____21 Feb 2019__________
Page 2 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
1. Introduction
This document is the EASA Approved Model List for STC SA00343BO for the installation of the Avidyne 700-00182-XXX and 700-00179-XXX GPS/Nav/Comm into eligible aircraft. Revisions to the AML must be coordinated through the STC holder, and require EASA approval.
IMPORTANT NOTICE
This STC is only applicable to CS 23 aircraft which are listed in this AML. Installations in CS 25, CS 27 and CS 29 aircraft are not authorized under this STC.
IMPORTANT NOTICE
With respect to the AML STC, the physical mounting of the antenna is specifically excluded from the approval in the case of installations on the pressure vessel of pressurized aircraft, composite aircraft, unless approved data is listed in the Master Document List of the STC.
EASA Approved Date: ____21 Feb 2019__________
Page 3 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
2. Approved Model List
Aircraft Make
Aircraft Model(s)
Aerostar Aircraft Corporation
PA-60-600 (Aerostar 600), PA60-601 (Aerostar 601), PA-60601P (Aerostar 601P), PA-60602P (Aerostar 602P), PA-60700P
Type Certificate Number
US A17WE
Model Specific Information
PA-60-601P/602P/700P require previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Air Tractor Inc.
AT-250, AT-300, AT-301, AT302, AT-400, AT-400A
AT-401, AT-401A, AT-401B, AT402, AT-402A, AT-402B, AT-501, AT-502, AT-502A, AT-502B, AT503, AT-503A
US A9SW US A17SW
Alexandria Aircraft, LLC
(Bellanca)
AT-602, AT-802, AT-802A 17-30, 17-31, 17-31TC
17-30A, 17-31A, 17-31ATC
American
8KCAB, 8GCBC
Champion Aircraft
7ECA, 7GCAA, 7GCBC (160HP), 7GCBC (180HP)
ASI Aviation F406 (Reims)
Aviat Aircraft, Inc. A-1, A-1A, A-1B, A-1C-180
S-1S, S-2A, S-2S, S-2B, S-2C
Beechcraft Corporation (Textron Aviation)
19A, B23, B19, C23, M19A, A24, 23, A24R, A23, B24R, A23A, C24R, A23-19, A23-24
US A19SW US 1A3
US A18CE
US A21CE
US A-759
EASA.A.109 (A54EU)
EASA.IM.A.294 (A11EA) US A8SO
US A1CE
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA Approved Date: ____21 Feb 2019__________
Page 4 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Beechcraft Corporation (Textron Aviation)
Aircraft Model(s)
H35, J35, K35, M35, 35-33, N35, 35-A33, 35-B33, P35, S35, 35C33, E33, F33, V35, V35A, V35B, 35-C33A, E33A, E33C, 36, A36, F33A, F33C, G33, A36TC, B36TC G36
95, B95, 95-55, 95-A55, B95A, D95A, E95, 95-B55, 95-B55A, 95-B55B, 95-C55, D55, 95C55A, D55A, E55, E55A, 56TC, A56TC, 58, 58A G58
58P, 58PA, 58TC, 58TCA
50, B50, C50, D50, D50A, D50B, D50C, D50E, D50E-5990, E50, F50, G50, H50, J50 B200, B200C, B200GT, B200CGT, B300, B300C
200, A100-1, 200C, 200CT, 200T, A200, A200C, A200CT, B200CT, B200T, 300,300LW, 1900, 1900C, 1900D 99, 99A, A99, A99A, B99, C99, 100, A100 (U-21F), A100A, B100 F90
60, A60, B60
76 77 65, 65-A90-1, A65, 65-A90-2, A65-8200, 65-A90-3, 65-80, 65A90-4, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, 70, B90, C90, E90, H90,
Type Certificate Number US 3A15
EASA.IM.A.279 (3A15) US 3A16
EASA.IM.A.280 (3A16)
US A23CE
US 5A4
EASA.IM.A.277 (A24CE) US A24CE
US A14CE
US A31CE
US A12CE
US A29CE US A30CE US 3A20
Model Specific Information
58P, 58PA require previously installed GPS antenna(s) to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval. Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval. 100, A100, A100A, B100 require previously installed GPS antenna(s) to utilize this STC for installation approval. Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval. Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA Approved Date: ____21 Feb 2019__________
Page 5 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make Beechcraft Corporation
(Textron Aviation)
Bernd Hager/Anatoli Strobbe GbR (Ruschmeyer Luftfahrttechnik
GmbH) Britten-Norman
Aircraft LTD
Cessna Aircraft Company
(Reims Aviation)
Aircraft Model(s) C90A, C90GT, C90GTi 390 (Premier I, Premier IA) R90-230RG
Type Certificate Number
EASA.IM.A.503 (3A20)
EASA.IM.A.073 (A00010WI)
EASA A.539
Model Specific Information
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
BN2A-8, BN2A-20, BN2A-21, BN2A-26, BN2A-27, BN2B-20, BN2B-21, BN2B-26, BN2B-27, BN2T, BN2T-4R, BN2A-9 BN2
BN2A
BN2A-2
BN2A-3
BN2A-6
BN.2A MK III, BN.2A MK III-2, BN.2A MK III-3 F150F, F150G, F150H, F150J, F150K, F150L, FA150L, F150M, FA150K, FA150M, F152, FA152, FRA150L, FRA150M F172D, F172E, F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P, FP172D FR172E, FR172F, FR172G, FR172H, FR172J, FR172K F177RG F182P, F182Q, FR182 F337E, FT337E, F337F, FT337F, F337G, FT337GP, F337H, FT337HP
EASA.A.388 (A17EU)
AAN 9405.1 (A17EU)
AAN 10101 (A17EU)
AAN 10918 (A17EU)
AAN 11105 (A17EU)
AAN 11108 (A17EU) UK BA6 (A29EU) US A13EU
US A4EU
US A18EU
US A26EU US A42EU US A23EU
EASA Approved Date: ____21 Feb 2019__________
Page 6 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
Cirrus Design Corporation
SR-20, SR-22, SR22T
SF50
Type Certificate Number
EASA.IM.A.007 (A00009CH)
EASA.IM.A.615
Model Specific Information
Wire Harness overbraid is required for IFR Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Commander Aircraft
Corporation
Cub Crafters, Inc.
112, 114, 112TC, 112B, 112TCA, 114A, 114B, 114TC
CC19-180
Diamond Aircraft Industries Inc.
(Canada)
DA 20-A1, DA 20-C1
Diamond Aircraft Industries GmbH
(Austria)
DA 40, DA 40F, DA 40NG, DA 42, DA 42M-NG, DA 42NG
DA 62
Dynac Aerospace Corp.(Aero Commander)
Embraer S.A.
(Aero Commander) 100 EMB-110P1, EMB-110P2
Extra
EA 300, EA 300/L, EA 300/LC,
EA 300/S, EA 300/200
Fuji Heavy
FA-200-160
Industries LTD.
(A00018CH) US A12SO
EASA.IMA.A.638 (A00053SE)
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA.IM.A.223 (TA4CH)
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA.IM.A.022 (A47CE)
EASA.A.005 (A57CE)
EASA.IM.A.629 (A57CE)
US 1A21
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
BR EA-7202 (A21SO)
EASA.A.362 (A67EU)
JP 20-10 (A4PC)
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA Approved Date: ____21 Feb 2019__________
Page 7 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
FA-200-180
FA-200-180AO
GA8 Airvan (Pty) Ltd
GA8, GA8-TC 320
Type Certificate Number
JP 22-2 (A4PC) JP 22-6 (A4PC) EASA.IM.A.042 (A00011LA)
Model Specific Information
GROB Aircraft AG
G120A
G115, G115A, G115B, G115C, G155C2, G115D, G115D2, G115EG G120TP-A
G520, G520T
Interceptor
200D
Aviation Inc.
EASA.A.075 (A49CE)
EASA.A.364 (A57EU)
EASA.A.565 (A00067CE)
DE 2066 (A63EU) US 3A18
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements. Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Learjet
Leonardo S.p.A. (Aermacchi S.p.A.)
Liberty (Discovery)
M7 Aerospace LLC (Fairchild)
23
F.260, F.260B, F.260C, F.260D, F.260E, F.260F S.205-18/F, S205-18/R, S.20520/F, S205-20/R, S.205-22/R, S208, S.208A XL-2
SA26-T, SA26-AT, SA226-T, SA226-AT, SA226-T(B), SA227AT, SA227-TT SA-226-TC, SA227-AC, SA227BC, SA227-PC SA227-CC, SA227-DC
US A5CE
EASA.A.586 (A10EU)
EASA.A.587 (A9EU)
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA.IM.A.343 (A00008DE)
US A5SW US A8SW
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
US A18SW
Maule Aerospace Technology, Inc.
Bee Dee M-4, M-5-180C, MXT7-160, M-4, M-4-180V, MX-7180A, M-4C, M-5-210C, MXT-7180A, M-4S, MX-7-180B, M-4T,
EASA.IM.A.018 (3A23)
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
EASA Approved Date: ____21 Feb 2019__________
Page 8 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Mitsubishi Heavy Industries, Ltd.
Mooney Aircraft Corp.
Pacific Aerospace Limited
Piaggio Aero Industries S.p.A.
Pilatus Aircraft Limited
Aircraft Model(s)
M-5-235C, M-7-235B, M-6-235, M-4-210, M-7-235, MX-7-180C, M-4-210C, MX-7-235, MX-7180, MX-7-180A, MX-7-180B, M4-220, MXT-7-180, MX-7-180B, M-4-220C, MT-7-235, M-4-220S MU-2B-25, MU-2B-26, MU-2B35, MU-2B-36, MU-2B-26A, MU2B-36A, MU-2B-40, MU-2B-60 MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B26 MU-2B-30, MU-2B-35, MU-2B36
M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20S M20M, M20R
750XL
P.166, P.166B, P.166C, P.166 DL3
P.180 Series Avanti, Avanti II
PC-12, PC-12/45, PC-12/47, PC-12/47E
Type Certificate Number
US A10SW
JP 19 (A2PC) JP 25 (A10SW) US 2A3
EASA.IM.A.266 (2A3)
EASA.IM.A.081 (A50CE)
EASA.A.384 (7A4)
EASA.A.059 (A59EU)
EASA.A.089 (A78EU)
PC-6, PC-6-H1, PC-6-H2, PC6/350, PC-6/350-H1, PC-6/350H2, PC-6/A, PC-6/A-H1, PC-6/AH2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC6/C-H2, PC-6/C1-H2
CH F 56-10 (7A15)
Model Specific Information Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval. Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Piper Aircraft
PA-28-140, PA-28-160, PA-28150, PA-28-151, PA-28-161, PA28-180, PA-28S-160, PA-28S180, PA-28-235, PA-28R-180, PA-28R-200, PA-28-181 (Archer II), PA-28R-201, PA-28R-201T, PA-28RT-201, PA-28-201T, PA28-236, PA-28RT-201T
US 2A13
EASA Approved Date: ____21 Feb 2019__________
Page 9 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make Piper Aircraft
Aircraft Model(s)
PA-32R-301T, PA-32-301FT, PA-32-301XTC, PA-32R-301 (HP)
PA-32-260, PA-32-300, PA-32S300, PA-32R-300, PA-32RT300, PA-32RT-300T, PA-32R301 (SP), PA-32-301,PA-32301T
Type Certificate Number
EASA.IM.A.239 (A3SO)
US A3SO
Model Specific Information
PA-23-235, PA-E23-250, PA-23250 PA-30, PA-39, PA-40
PA-31, PA-31-300, PA-31-325, PA-31-350 PA-31P, PA-31T, PA-31T1, PA31T2, PA-31T3, PA-31P-350
PA-24, PA-24-250, PA-24-260, PA-24-400
US 1A10 US A1EA US A20SO US A8EA
US 1A15
PA-31P requires previously installed GPS antenna(s) to utilize this STC for installation approval.
Polskie Zaklady Lotnicze SP.
PA-34-200, PA-34-200T, PA-34220T(Seneca IV) PA-34-220T (Seneca V) PA-42, PA-42-720, PA-42-1000
PA-42-720R
PA-44-180, PA-44-180T PA-38-112 PA-28-181 (Archer III) PA-46-310P, PA-46-350P, PA46R-350T, PA-46-500TP
PZL M18, PZL M18A, PZL M18B PZL M26 01
US A7SO
EASA.IM.A.090 (A7SO)
US A23SO
US A32SO
EASA.IM.A.232 (A19SO) US A18SO
EASA.IM.A.234 (2A13)
EASA.IM.A.077 (A25SO)
EASA.A.056 (A47EU)
EASA.A.057 (A44CE)
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval. Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA Approved Date: ____21 Feb 2019__________
Page 10 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
PZL M28 05
Type Certificate Number
EASA.A.058 (A56CE)
Model Specific Information
PZL WARSZAWAOKECIE S.A.
Quest Aircraft Design LLC REVO, Inc.
RUAG Aerospace Services GmbH
(Dornier)
PZL-104 WILGA 80, PZL-104M WILGA 2000, PZL-104MA WILGA 2000 PZL-KOLIBER 150A, PZLKOLIBER 160A
Kodiak 100
LA-4A, LA-4P, Lake LA-4-200, Lake Model 250 Do 28 D, Do 28 D-1,
Dornier 228-100, Dornier 228101, Dornier 228-200, Dornier 228-201, Dornier 228-202, Dornier 228-212
EASA.A.061 (A55EU)
EASA.A.091 (A69EU)
EASA.IM.A.632 (A00007SE) US 1A13
EASA.A.360 (A8IN)
EASA.A.359 (A16EU)
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Slingsby Advanced Composites
T67M260, T67M260-T3A
EASA.A.390 (A73EU)
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
SOCATA
Rallye 100S, Rallye 150T, Rallye150ST, MS880B, MS885
MS892A-150, MS892E-150, MS893A, MS893E, MS894A, MS894E, Rallye 235C, Rallye235E
TB9, TB10, TB20, TB21, TB200
TBM 700A, TBM700B, TBM700C1, TBM700C2, TBM700N
GA-7 (Cougar)
SST Flugtechnik GmbH
(Extra)
EA 400, EA 400-500
EASA.A.377 (7A14)
EASA.A.379 (7A14)
EASA.A.378 (A51EU)
EASA.A.010 (A60EU)
FR TCDS 190 (A17SO)
EASA.A.011 (A43CE)
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Wire Harness overbraid is required for IFR installations. Reference the Installation Manual for installation requirements.
EASA Approved Date: ____21 Feb 2019__________
Page 11 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
Type Certificate Number
Model Specific Information
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Symphony Aircraft Industries
Textron Aviation Inc.
OMF-100-160
150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150K, A150L, A150M, 152, A152 170, 170A, 170B
172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172Q, 172R, 172S,
EASA.IM.A.031 (A46CE) US A319
US A799 US 3A12
172RG, 175, 175A, 175B, 175C, P172D, R172E, R172F, R172G, R172H, R172J, R172K
US 3A17
172R, 172S 175, 175A, 175B, 175C
EASA.IM.A.051 (3A12) US 3A17
177, 177A, 177B
US A13CE
177RG
US A20CE
180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K
182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N 182P, 182Q, 182R, R182, T182,TR182
182S, 182T, T182T
185, 185A, 185B, 185C, 185D, 185E, A185E, A185F
188, 188A, 188B, A188, A188B, T188C
190, 195, 195A, 195B
US 5A6
US 3A13
EASA.IM.A.052 (3A13) US 3A24 US A9CE
US A-790
206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, U206, U206A, U206B, U206C,
US A4CE
EASA Approved Date: ____21 Feb 2019__________
Page 12 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
(Cessna)Textron Aviation Inc. (Cessna)
Aircraft Model(s)
U206D, U206E, U206F, U206G 206H, T206H
207, 207A, T207, T207A 208, 208B
210, 210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L, 210M, 210N, 210R, 210-5 (205), 210-5A (205A), P210N, P210R, T210F, T210G, T210H, T210J, T210K, T210L, T210M, T210N, T210R T303 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, 310I, 310J, 310J-1, 310K, 310L, 310N, 310P, E310H, E310J, T310P, 310Q, T310Q, 310R, T310R 320, 320-1, 320A, 320B, 320C, 320D, 320E, 320F 340, 340A, 335
336
337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, M337B, P337H, T337B, T337C, T337D, T337E, T337F, T337G, T337H, T337H-SP 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425 404 LC41-550FG, LC42-550FG
441
501, 551
Type Certificate Number
Model Specific Information
EASA.IM.A.053 (A4CE)
US A16CE
EASA.IM.A.226 (A37CE) US 3A21
P210N, P210R require previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
US A34CE US 3A10
US 3A25
US A2CE US A6CE
340, 340A, 335, require previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
T337G, P337H require previously installed GPS antenna(s) to utilize this STC for installation approval.
US A7CE
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
US A25CE EASA.IM.A.516 (A00003-SE)
US A28CE
US A27CE
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
The aircraft's equipment list must be updated for single pilot operation
Requires previously installed GPS
EASA Approved Date: ____21 Feb 2019__________
Page 13 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
Textron Aviation Inc.
(Cessna)
525, 525A, 525B, 525C
Type Certificate Number
EASA.IM.A.078 (A1WI)
Model Specific Information
antenna(s) or separate approval to utilize this STC for installation approval.
The aircraft's equipment list must be updated for single pilot operation.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
True Flight Holdings LLC
(Grumman American)
Twin Commander Aircraft LLC
AA-1, AA-1A, AA-1B, AA-1C
AA-5, AA-5A, AA-5B, AG-5B
500, 500-A, 500-B, 500-U, 500S, 520, 560, 560-A, 560-E 560-F, 680, 680E, 680F, 680FL, 680FL(P), 680T, 680V, 680W, 681, 685, 690, 690A, 690B, 690C, 690D, 695, 695A, 695B, 720 700
Viking Air Limited (de Havilland Inc.)
Vulcanair S.p.A. (Partenavia Costruzioni Aeronauticas S.p.A.)
DHC-2 Mk. III
DHC-6-1, DHC-6-100, DHC-6200, DHC-6-300 DHC-6-400
P.68, P.68B, P.68C, P.68C-TC, P.68 Observer, P.68 "Observer 2", P.68-TC "Observer", AP68TP-300 "Spartacus", AP68TP-600 "Viator", P.68R SF600, SF600A
WACO Classic Aircraft Corp.
2T-1A, 2T-1A-1, 2T-1A-2 YMF F5, YMF F5C
Zenair
CH2000
Zlin Aircraft A.S. Z-242L
Z-143L
US A11EA
US A16EA US 6A1 US 2A4
US A12SW
CA A-22 (A-806) CA A-82 (A9EA) EASA.A.385 (A31EU)
690, 690A, 690B, 690C, 690D, 695, 695A, 695B, 700, 720 require previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
Requires previously installed GPS antenna(s) or separate approval to utilize this STC for installation approval.
EASA.A.608 (A61EU) US A18EA
EASA.IM.A.055 (ATC 542) CA A-185 (TA5CH) EASA.A.027 (A76EU) EASA.A.028 (A76EU)
EASA Approved Date: ____21 Feb 2019__________
Page 14 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
EASA Approved Model List for STC SA00343BO
Aircraft Make
Aircraft Model(s)
ZLIN 526L
Type Certificate Number
EASA.A.353 (A30EU)
Model Specific Information
EASA Approved Date: ____21 Feb 2019__________
Page 15 of 15
AVIFD-485 Rev: 03, Date: 02/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX Integrated Flight Display
AML STC Master Document List STC No. SA00343BO
4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742
Document Number AVIFD-306
Control Category N/A
Revision Description
ECO
Date
01
Updates for software 10.0.1.0
ECO-14-283 08/26/14
02
Updates for software 10.0.2.0
ECO-14-356 11/14/14
03
Updates for software 10.0.3.0
ECO-14-424 01/26/15
04
Updates for 10.1, 700-00179-XXX ECO-15-187 05/27/15
05
IM Revision for MLB100 edits
ECO-15-385 09/25/15
06
WiFi/Bluetooth Updates
ECO-15-468 11/06/15
07
Updates for software 10.1.1.0
ECO-15-490 11/18/15
08
Updates for software 10.1.2.0
ECO-16-054 03/01/16
09
EASA Updates, add Air Tractor to AML
ECO-16-185 06/06/16
10
Updates for software 10.1.3.0
ECO-16-182 06/23/16
11
TIA support for software 10.2.0.
ECO-17-054 02/28/17
12
Update ADSB Notes in IM
ECO-17-060 03/08/17
13
Update to IM and AFMS
ECO-17-066 03/16/17
14
Update for EASA AFMS and Checklist
ECO-17-237 09/07/17
15
Updates for software 10.2.1.0
ECO-18-013 02/09/18
16
IM, EASA AML, Pilot Guides
ECO-18-066 04/11/18
17
Updates for 10.2.2
ECO-18-135 05/29/18
18
Add Proline AFMS
ECO-18-160 05/30/18
19
Update for GPS roll-over of the 10 bit number of weeks, IM update
ECO-19-025
02/08/19
20
Added Ruschmeyer R90-230RG to AML
ECO-19-035 02/14/19
21
Updates for 10.2.3.1, add TDR94 Transponder report
ECO-19-050 04/17/19
Confidential property of Avidyne Corporation Not to be disclosed without permission
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX AML STC Master Document List
Table of Contents
1. Purpose....................................................................................3 2. Master Document List Applicable to All Aircraft.................4
2.1 Substantiation Data List Compliance Data............................................................... 4 2.2 Installation Data List .................................................................................................. 6 2.3 Manufacturer's Supporting Data List .......................................................................... 6 2.4 EASA STC 10058132 Supporting Data List................................................................ 6
UP793797
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 2 of 6
AVIFD-306 Revision: 21, Date: 04/17/1902/14/19
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX AML STC Master Document List
1. Purpose
This Master Document List is for the Avidyne 700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX Integrated Flight Display, STC SA00343BO. Section 2 lists all applicable documents that support the installation of the Integrated Flight Display and associated components into various aircraft.
UP793797
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 3 of 6
AVIFD-306 Revision: 21, Date: 04/17/1902/14/19
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX AML STC Master Document List
2. Master Document List Applicable to All Aircraft
2.1 Substantiation Data List Compliance Data
Document Source
Avidyne
Document Number AVIFD-310 AVIFD-305
AVIFD-306
AVIFD-307 AVIFD-308 AVIFD-309 AVIFD-311
AVIFD-312 AVIFD-313 AVIFD-314 AVIFD-315
AVIFD-316
AVIFD-317 AVIFD-318 AVIFD-320 AVIFD-340
AVIFD-342 AVIFD-343 AVIFD-414 AVIFD-424 AVIFD-425 AVIFD-426 AVIFD-427 AVIFD-428 AVIFD-415
Revision
Description
05
700-00182-XXX IFD540 Nav/Comm/GPS in Approved Model List STC Certification Plan
03
700-00182-000/700-000179-XXX Integrated Flight Display Functional Hazard Assessment
21
700-00182-XXX/700-00179-XXX Integrated Flight Display AML STC Master Document List
04
700-00182-XXX Integrated Flight Display System EMI and Functional Ground Test Plan
01
700-00182-XXX IFD540 Nav/Comm/GPS Navigator Flight Test Plan
02
Avidyne 700-00182-XXX IFD540 Structural Analysis Report
03
700-00182-XXX IFD540 Nav/Comm/GPS Electrical Load Analysis Cessna 182P N1291S
02
700-00182-XXX Integrated Flight Display Lightning Indirect Effect and HIRF
05
700-00182-XXX Nav/Comm/GPS System Safety Assessment
00
700-00182-XXX Integrated Flight Display Compliance Report
09
700-00182-XXX Integrated Flight Display Instructions for Continued Airworthiness
02
700-00182-XXX IFD AML STC Environmental Compatibility Report
00
700-00182-XXX IFD540 Nav/Comm/GPS Navigator Flight Test Report
05
700-00182-XXX Integrated Flight Display AML STC Approved Model List
01
ITL Integration Verification Test Report
00
700-00182-XXX Integrated Flight Display System EMI and Functional Ground Test Report
04
700-00182-XXX Integrated Flight Display AML Model Qualification Process
04
700-00182-XXX Model Qualification Report
02
700-00182-XXX and 700-00179-XXX Certification Plan, 10.1
00
700-00182-XXX and 700-00179-XXX Ground Test Plan, 10.1
02
700-00182-XXX and 700-00179-XXX Flight Test Plan, 10.1
00
700-00182-XXX and 700-00179-XXX Release 10.1 Compliance Report
01
700-00182-XXX and 700-00179-XXX Flight Test Report, 10.1
00
700-00182-XXX and 700-00179-XXX Ground Test Report, 10.1
00
700-00182-XXX and 700-00179-XXX Ground Test Plan 10.1 WiFi/Bluetooth
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 4 of 6
AVIFD-306 Revision: 21, Date: 04/17/1902/14/19
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX AML STC Master Document List
Document Source
Document Number AVIFD-416 AVIFD-417 AVIFD-418 AVIFD-431 AVIFD-471 AVIFD-476 AVIFD-477 AVIFD-478 AVIFD-479 AVIFD-480 AVIFD-481 AVIFD-521 AVIFD-522 AVIFD-523 AVIFD-524 AVIFD-551 AVIFD-593
600-00298-000
600-00298-002
Revision
Description
01
700-00182-XXX and 700-00179-XXX Flight Test Plan 10.1 WiFi/Bluetooth
00
700-00182-XXX and 700-00179-XXX Compliance Report 10.1 WiFi/Bluetooth
00
700-00182-XXX and 700-00179-XXX Flight Test Report 10.1 WiFi/Bluetooth
04
700-00182-XXX and 700-00179-XXX Certification Plan, WiFi/Bluetooth
00
700-00182-XXX and 700-00179-XXX Flight Test Report 10.1.1.0
05
Avidyne 700-00182-XXX IFD5XX and 700-00179-4XX IFD-4XX s/w Release 10.2 Certification (amendment) Plan
00
Avidyne 700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX s/w Release 10.2 Ground Test Plan
01
Avidyne 700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX s/w Release 10.2 Flight Test Plan
00
Avidyne 700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX s/w Release 10.2 STC Compliance Report
00
Avidyne 700-00182-XXX IFD5XX and 700-00179-XXX IFD-4XX s/w Release 10.2 Flight Test Report
00
Avidyne 700-00182-XXX IFD5XX and 700-00179-XXX IFD-4XX s/w Release 10.2 Ground Test Report
00
AFS ADSB Out Data IFD/GTX330ES, Release 10.2
00
AFS ADSB Out Data IFD/GTX345, Release 10.2
00
ADSB Out IFD/GTX330ES, Release 10.2 Test Results
00
ADSB Out IFD/GTX345, Release 10.2 Test Results
00
Minor Change for Integrated Flight Display STC Sa00343BO release 10.2.2 and Collins Proline Avionics
00
TDR94 Transponder, Detailed Analysis of Flight Test Data N43BH
Airplane Flight Manual Supplement for Installations with the 700-
07
00182-XXX and 700-00179-XXX IFD540/440 Integrated Flight
Display
01
Avidyne Integrated Flight Displays p/n 700-00182-XXX and 70000179-XXX installed with Collins ProLine 21 Avionics
UP793797
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 5 of 6
AVIFD-306 Revision: 21, Date: 04/17/1902/14/19
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
700-00182-XXX IFD5XX and 700-00179-XXX IFD4XX AML STC Master Document List
2.2 Installation Data List
Document Source
Document Number
Revision
Description
Avidyne
600-00299-000 600-00298-000
AVIFD-315 600-00298-002
17
IFD540/440 Installation Manual
07
Airplane Flight Manual Supplement for Installations with the 70000182-XXX and 700-00179-XXX Integrated Flight Display
09
700-00182-XXX and 700-00179-XXX Integrated Flight Display Instructions for Continued Airworthiness
01
Avidyne Integrated Flight Displays p/n 700-00182-XXX and 70000179-XXX installed with Collins ProLine 21 Avionics
2.3 Manufacturer's Supporting Data List
Document Source
Document Number
Revision
Description
Avidyne/ Bendix King
600-00300-001 600-00304-000 89000039-010 89000041-008 600-00317-000 600-00318-000 600-00319-000
07
IFD5XX Series Integrated Flight Display Pilot Guide
07
IFD4XX Series Integrated Flight Display Pilot Guide
00
Bendix King AeroNav 900 and 910
00
Bendix King AeroNav 800
03
IFD550 and IFD545 Pilot's Guide
03
IFD510 Pilot's Guide
03
IFD410 Pilot's Guide
2.4 EASA STC 10058132 Supporting Data List
Document Source
Document Number
Revision
Description
Avidyne
600-00298-001
AVIFD-484 AVIFD-485
03
Airplane Flight Manual Supplement for Installations with the 70000182-() and 700-00179-XXX Integrated Flight Display - EASA
02
IFD5XX/IFD4XX EASA Installation Checklist
03
IFD5XX/IFD4XX EASA Approved Model List
UP793797
Confidential property of Avidyne Corporation Not to be disclosed without permission
Page 6 of 6
AVIFD-306 Revision: 21, Date: 04/17/1902/14/19
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742
FAA Approved Airplane Flight Manual Supplement
For _________________________________
Make and Model Airplane
with Avidyne Integrated Flight Displays p/n 700-00182-XXX and 70000179-XXX
Registration No. _________
Serial No. __________
This supplement must be attached to the applicable FAA Approved
Airplane Flight Manual when Avidyne 700-00182-XXX Integrated
Flight Display (IFD) and/or 700-00179-XXX Integrated Flight
Display installed in accordance with STC SA00343BO. The
information contained herein supplements or supersedes the basic
manual only in those areas listed. For limitations and procedures not
contained in this supplement consult the basic Airplane Flight
Manual.
WILLIAM P Digitally signed by WILLIAM P WITZIG
WITZIG Date: 2019.05.03
FAA Approved _________________14_:2_5_:2_8_-_04_'0_0_' __
0DQDJHU1RUWKHDVW)OLJKW7HVW6HFWLRQ
)HGHUDO$YLDWLRQ$GPLQLVWUDWLRQ
%XUOLQJWRQ0$
FAA APPROVED Date:
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LOG OF REVISIONS
Revision Number
00 01
02 03
04 05
06
07
Revised Pages
Description of Revisions
FAA Approval
ALL Pages 1,2, 3, 4, 5, 6, 7, 8, 9, 11, 15,
16, 17, 18, 21 Pages 13, 14, 19 Pages 2, 3, 4, 7, 8. 9, 10, 11, 12, 13, 18, 19, 20, 21,
24 Pages 4 - 24
Pages 11, 13, 22
Pages 13
Pages 4, 5, 8, 26
Initial Release
Add IFD440 and Software Release 10.1.0.0
Robert Mann -
AEG comments
Add models IFD410, IFD510, IFD545, IFD550 and software version 10.2
Robert Mann -
Added 91.227 compliance
-
statement
Added limitation regarding use of radar display, added
EmProc for disabling wireless connectivity.ACO comments incorporated
Anthony Pigott
Added note regarding IFD4XX FLTA aural alert conflicts with other sensors
Anthony Pigott
Added TDR ADS-B out compliance statement, BK
pilot guide references, ADS-B in only limitations
::LW]LJ
Date Jul 24 2014
Jun 18 2015
-
Mar 06 2017
Mar 20 2017
A vertical black line in the margin shows revised portions of affected pages.
FAA APPROVED Date:
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P/N 600-00298-000 Rev 07
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Section 1 General
This airplane is equipped with an Avidyne p/n 700-00182-XXX IFD5XX Integrated Flight Display (IFD) and /or Avidyne p/n 70000179-XXX IFD4XX Integrated Flight Display. Both part numbers may be referred to in this document as simply IFD.
The IFD contains a GPS (SBAS) receiver (all IFD models), VHF Nav/Com transceiver (IFD440, IFD540 and IFD550) and processing to accomplish control, display, navigation and input/output to other avionic systems. The IFD 545 and IFD550 include an internal ARS and are capable of displaying attitude information and ego-centric synthetic vision (SVS).
GPS/SBAS TSO-C146c Class 3 Operation The IFD4XX and IFD5XX has airworthiness approval for navigation using GPS and SBAS (Satellite Based Augmentation System complying with ICAO Annex 10) for IFR en route, terminal area, and non-precision approach operations ("GPS", "or GPS", and "RNAV (GPS)" approaches). The IFD4XX and IFD5XX are approved for approach procedures with vertical guidance including "LPV" and "LNAV/VNAV" and approaches without vertical guidance including "LP" and "LNAV".
The IFD4XX and IFD5XX comply with the requirements for GPS Class II oceanic and remote navigation (RNP-10) and (RNP-4) without time limitations. A second navigation source may be required for these operations to meet availability requirements.
Database Accuracy and Completeness The operator is responsible to ensure that the navigation data used in the unit has the accuracy, resolution, and timeliness appropriate for the purpose of the flight operation being conducted. Using navigation data from an Avidyne authorized supplier will ensure that the navigation data has the same accuracy and resolution provided by
FAA APPROVED Date:
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Avidyne requests that any observed database discrepancies are reported. These discrepancies may be in the form of an incorrect procedure, incorrectly identified terrain, obstacles, navigation fixes, or any other displayed item used for navigation or communication in the air or on the ground. Use the Service Hotline listed on the back cover of the IFD4XX and IFD5XX Pilot Guides.
Avidyne accurately processes and validates the database data, but cannot guarantee the accuracy and completeness of the data provided by various state sources and their suppliers.
Avidyne Corporation holds a FAA Type 2 Letter of Acceptance (LOA) in accordance with AC 20-153 for database integrity, quality, and database management practices for the navigation database. Flight crew and operators can view the LOA at www.avidyne.com.
ADS-B OUT Compliance The IFD4XX and/or IFD5XX installed per this STC in conjunction with the following transponders/ UAT transceivers have been shown to meet the equipment requirements of 14 CFR 91.227 for ADS-B OUT:
Garmin GTX330ES Garmin GTX335/345 Collins TDR94(D)
IFD4XX and IFD5XX have been approved for ADS-B Out compliance with other transponders under separate installation approvals (STCs). Check the aircraft's transponder or UAT transceiver AFMS for the statement above indicating ADS-B out compliance for the navigator and transmitter combination.
ADS-B In Only The IFD4XX and/or IFD5XX installed per this STC may be interfaced with an ADS-B UAT or 1090MHz receiver (ADS-B In) that does not provide ADS-B out capability. If no ADS-B out system is installed, this installation will not be able to receive TIS-B client status, and will not receive ADS-R or TIS-B broadcasts from ATC
FAA APPROVED Date:
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Figure 1. Avidyne IFD540 700-00182-XXX Integrated Flight Display (IFD).
USB Port
Volume / Power / Squelch Knob
CDI Nav Source Knob Frequency Swap
Ambient Light Sensor
Line Select Keys
Com/Nav Manual Tuning Knob
Latch
Page Function Keys
Dedicated Function Keys
Context Sensitive IFD Knob
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Figure 2. Avidyne IFD440 700-00179-XXX Integrated Flight Display (IFD).
Volume / Power / Squelch Knob
Frequency Swap
Line Select Keys (LSKs)
CDI Nav Source Knob
Ambient Light Sensor
Dedicated Function Keys
Cam Latch
Com/Nav Manual Tuning Knob
Page Function Keys
USB Port
Context Sensitive IFD Knob
FAA APPROVED Date:
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Figure 3. Avidyne IFD550 700-00182-XXX Integrated Flight Display Ego-centric SVS.
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Section 2 Limitations
1. The appropriate IFD4XX and IFD5XX Integrated Flight Display Pilot Guides must be available to the pilot during all flight operations:
P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800 P/N 600-00317-000 for the IFD545 and IFD550 P/N 600-00318-000 for the IFD510 P/N 600-00319-000 for the IFD410
2. For Class I airplanes (single engine, piston, under 6,000# GTOW), a single IFD5XX or IFD4XX is sufficient for flight under instrument flight rules (IFR). IFR is prohibited when the GPS or VHF navigation receiver is inoperable unless the airplane has an additional approved GPS and/or VHF receiver.
For all other Airplanes (Class II, III and IV), dual VHF communications transceivers and dual GPS or VHF Navigation receivers are required for flight under instrument flight rules (IFR). One communication transceiver, or one GPS receiver, or one VHF navigation receiver may be inoperable for IFR flight.
In all airplanes, an approved navigation display (external CDI, HSI, or EHSI) is required for flight under instrument flight rules (IFR).
3. The IFD4XX and/or IFD5XX installed with an SBAS approved antenna, provides pilot and automatic flight control guidance for the following operations conducted under instrument flight rules (IFR): x VOR, LOC, ILS instrument approach procedures (procedures using VHF radio guidance) IFD440, IFD540, IFD550 only
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x RNP instrument approach procedures using the following lines of minima: o LNAV minima (including when using advisory vertical guidance from the system); o LNAV/VNAV minima;
o LPV minima; and o LP minima. Note: The U.S. titles RNP instrument approach procedures "RNAV (GPS) Rwy XX". Other States may use similar titling or may title these procedures "RNAV (GNSS) Rwy XX". x RNP terminal procedures, including RNP arrival procedures and RNP departure procedures. x RNAV terminal procedures, including RNAV arrival procedures and RNAV departure procedures.
The IFD4XX and/or IFD5XX when installed with a nonSBAS antenna, provide pilot and automatic flight control guidance for the following operations conducted under instrument flight rules (IFR): x VOR, LOC, ILS procedures (procedures using VHF
radio guidance) IFD440, IFD540, IFD550 only; x RNP instrument approach procedures using the
following lines of minima: o LNAV minima.
x RNP terminal procedures, including RNP arrival procedures and RNP departure procedures.
x RNAV terminal procedures, including RNAV arrival procedures and RNAV departure procedures.
4. When GPS is available, the IFD440 and/or IFD540/550 , may serve as an RNAV alternate or substitute means of navigation for ground-based navigation aids that are out-ofservice or unavailable.
5. GPS/SBAS based IFR enroute, oceanic, and terminal navigation is prohibited unless current Navigation and Procedure databases are installed.
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6. Use of RNP terminal operations and RNP instrument approach procedures containing RF leg segments (identified on the approach plate) is prohibited.
7. In areas where SBAS coverage is not available, the pilot must check RAIM availability.
8. The Avidyne moving map display provides visual depiction of the aircraft's own-ship, GPS position on a moving map for situational awareness (SA) purposes only. The pilot shall not use the moving map display as a sole means of navigation. The external CDI, HSI, or EHSI display must be used as the primary navigation instrument.
9. The Avidyne electronic checklists display supplements the Pilot Operating Handbook checklists and are advisory only. The pilot shall not use the electronic checklists as the primary set of on-board aircraft checklists. FAA Approved Flight Manual paper checklist must be available to the pilot as the primary reference.
10. The IFD integrates with separately approved system installations such navigation indicators, remote annunciators. Adherence to limitations in installation AFM supplements for those systems is mandatory.
11. The use of datalink, traffic and lightning sensor information displayed on the IFD4XX and IFD5XX must be in compliance with the approved AFM supplements for those systems.
12. Gloves may not be used to operate the IFD4XX and IFD5XX touch functions unless the Glove Qualification Procedure located in the IFD4XX/IFD5XX Pilot's Guides has been successfully completed.
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13. The IFD545 and IFD550 may not be used for primary attitude information or standby attitude information (If required by type design). The IFD545 and/or IFD550 may only be used as a secondary (non-required) source for attitude information.
NOTE
The IFD545 and/or IFD550 may be used in conjunction with air data and turn rate indicators in determining if a primary or standby attitude source has failed e.g. in the case of primary/standby attitude indicator mis-compare.
14. The IFD545 and/or IFD550 may not be used for primary navigation deviation information (horizontal of vertical). The IFD545 and/or IFD550 may only be used as a secondary (non-required) source for this information.
15. The Avidyne IFD4XX and IFD5XX may only be operated in IMC conditions as a radar display when used in conjunction with an independent lightning detection and display system (Approved Thunderstorm Detection Equipment).
CAUTION
Terrain information shown on the MAP page display is provided to the pilot as an aid to situational awareness. The MAP page terrain color representations should not be used as a sole basis for terrain avoidance.
CAUTION
Traffic information shown on the Map page display is provided to the pilot as an aid to visually acquiring traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic. Avoidance maneuvers should not be made based only on a Traffic Advisory.
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CAUTION
In IFD545 and IFD550 units the inertial reference accelerometers may be irreparably damaged by exposure to temperatures below -40°C. The units are capable of operating at -40°C, but exposure to temperatures below this, even when powered off, can stress the parts internally causing a detectable and annunciated failure of the sensors.
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Section 3 Emergency Procedures
Loss of GPS In the event of the loss of the IFD440 or IFD540 GPS receiver, the FMS will enter dead reckoning mode for 5 minutes, after that all FMS functions are lost and the ownship is removed from map depictions. The pilot should revert to remaining navigation receiver (required for IFR operations).
Loss of VHF Nav/Com In the event of the loss of IFD440, IFD540 or IFD550 VHF navigation, the pilot should revert to remaining navigation receiver (required for IFR operations).
Warning Messages Caution and warning messages provided by the IFD4XX and IFD5XX are related to functions performed by the IFD4XX and IFD5XX and are additional to the caution and warning annunciation system provided by the aircraft.
NOTE
The original caution and warning annunciator panel remains as the primary indication. POH/AFM Emergency procedures are not affected by this installation.
CAUTION
IFD4XX units lack an audio inhibit output to preclude other sensors aural alerts from sounding while IFD4XX forward looking terrain awareness (FLTA) aural alerts are issued. Simultaneous alerts are possible. Example; a TIS-B aural traffic alert could be issued at the same time as an FLTA terrain or obstacle aural caution or warning.
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To Disable WiFi/Bluetooth Connectivity on IFD4XX/IFD5XX:
1. Press and hold the IFD4xx/IFD5XX power button/knob for 1 second (upper left bezel) --------------------------------------
2. ALLOW/IGNORE WiFi Bluetooth dropdown is presented. Press IGNORE--------------------------- Dropdown is removed
3. Verify the WiFi and Bluetooth icons on the upper right of the display are removed--------------------- Extinguish
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Caution Messages The Caution and Warning panel is not altered as part of this modification and remains the primary means of providing Caution and Warning messages.
Caution and Warning messages are provided in the following table:
EXCEEDANCES | WARNINGS RED
Short Text
Long Text
Terrain Pull-Up* Terrain Pull-Up
Warning Obstacle*
Warning Obstacle
Unit Overtemp Unit Unreliable
Unit Overtemp: <internal component name> Unit reliability in question Get IFD serviced
Low Volts off in <countdown from 60> sec
Pull Up
Low Volts IFD powers down in <countdown from 60> sec
Excessive Descent Rate
Comments
The FLTA algorithm has detected an imminent ground collision Initiate an immediate recovery maneuver.
The FLTA algorithm has detected an imminent obstacle collision.
Initiate an immediate recovery maneuver.
One or more of the internal components has exceeded its maximum design temperature and reliability cannot be ensured until the unit is tested by the Avidyne Service Center.
Contact the Avidyne Service Center or a local dealer for service. This message will be present on every subsequent power cycle until reset by the Avidyne Service Center.
Main supply voltage has fallen below 9 VDC. Contact a local dealer for service.
The TAWS Excessive Descent Rate algorithm has detected a CFIT potential initiate an immediate recovery maneuver.
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EXCEEDANCES | CAUTIONS YELLOW
Short Text Caution Terrain*
Long Text Caution Terrain
Caution Obstacle* Caution Obstacle
GPS Integrity Lost
GPS Integrity Lost Crosscheck Nav
GPS Fault Dead Reckoning
Position updated via dead reckoning
Comments
The FLTA algorithm is predicting a likely ground collision within approximately 60 seconds initiate a proper recovery maneuver.
The FLTA algorithm is predicting a likely obstacle collision with approximately 60 seconds initiate a proper recovery maneuver.
This is alerting about imminent exceedence of horizontal fault detection limits or protection levels.
Crosscheck the nav solution and determine the best course of action.
If on a GPS based approach, Missed Approach is required.
The system will use the last known position and groundspeed (and heading if available) to estimate the aircraft position following loss of GPS for up to 5 minutes. Since Dead Reckoning assumes no directional or groundspeed change, it will not be reliable even during those first 5 minutes if either or both of these factors have changed.
Execute a missed approach if this occurs while performing a GPS based approach. Use an alternate GPS or VHF navigation receiver.
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Short Text
Long Text
GPS Fault No Position
No position available
Configuration Error
Configuration Error IFD Requires Service
LPV Unavailable Use L/VNAV DA
GPS integrity is insufficient for LPV Approach
LPV Unavailable Use LNAV MDA
GPS integrity is insufficient for LPV Approach
LP Unavailable Use LNAV MDA
L/VNAV Unavail. Use LNAV MDA
VNAV Lost Use LNAV MDA
GPS integrity is insufficient for LP Approach
GPS integrity is insufficient for L/VNAV Approach
Excessive XTK or Low GPS Integrity for Vertical Guidance
Comments
The navigation solution cannot compute a position, typically after dead reckoning has expired.
Execute a missed approach if this occurs while performing a GPS based approach. Use an alternate GPS or VHF navigation receiver.
The configuration of the IFD or the devices to which it is communicating with has changed or experienced an error.
Contact the Avidyne Service Center or a local dealer for service.
Transition to a non-LPV approach and the appropriate minima if possible. Otherwise execute a missed approach.
Transition to a non-LPV approach and the appropriate minima if possible. Otherwise execute a missed approach.
Transition to a non-LP approach and the appropriate minima.
Transition to a non-L/VNAV approach and the appropriate minima.
Transition to LNAV minima.
FAA APPROVED Date:
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Short Text
Long Text
Check Altitude Too Low
Aircraft is below the glide slope altitude at FAF
Comments
Correct aircraft altitude as required to safely conduct the approach or initiate a climb to a published safe altitude and abort the approach.
Traffic Sensor Fault*
Traffic <Low | High> <Bearing in clock direction> <Distance in NM>*
No communication with traffic sensor (local) OR
Traffic sensor has failed (global)
Traffic [Brg (e.g. 1:00)] [dist (e.g. 2 NM)] [alt (e.g. 200 ft)]
Traffic <Low | High> <Distance in NM>*
Traffic <Distance in NM> <Signed relative altitude in feet> FT
Contact a local dealer for service.
Traffic advisories - Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Traffic advisories with no bearing information Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
FAA APPROVED Date:
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Short Text
Long Text
Traffic <Bearing in clock direction> <distance in NM>*
Traffic <bearing in clock direction> <distance in NM>
Traffic <distance in NM>*
Traffic <distance in NM>
COM TX Fault
Transmitter Fault, No TX Ability
COM Stuck TX
Stuck Mic Timeout, Transmitter Disabled
Comments
Traffic advisories with no relative altitude information Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Traffic advisories with no relative altitude information and no bearing Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Transition to a backup VHF com radio (if available) or initiate lost communication procedures. Contact the Avidyne Service Center or a dealer for service.
Requires 35 seconds of continuous transmission. Verify the PTT is stuck and contact a dealer for service as required.
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Short Text
Long Text
No Comm with VHF No communication with the VHF radio
Unit Overtemp Check cooling
Unit Overtemp: <internal component identification>
Comments
Transition to a backup VHF com radio (if available) or initiate lost communication procedures. Contact the Avidyne Service Center or a dealer for service.
One or more of the internal components has exceeded 80qC. Contact the Avidyne Service Center or a dealer for service consider adding a source of cooling and/or improving air flow in/around the IFD.
Low Volts
Backlight reduced to 25%
Main supply voltage has fallen to approximately 11VDC.
Check the aircraft alternators are on and functional.
Consider load shedding the power bus that is powering the IFD.
Manual Sequence Req'd
Heading Lost
Altitude invalid leg will not auto sequence
Using ground track for SVS
In basic E-M aircraft where the IFD does not have altitude input, this message will appear when the FMS active leg is a HeadingÆAltitude leg. In this case, the FMS flight plan will need to be manually sequenced to the next leg. Failure to do so will keep the FMS flying the heading indefinitely.
Indicates loss of the TVV and the aircraft reference symbol ("wedge") now points at ground track, not aircraft heading. "TRK" will also be displayed below the digital compass on the SVS page.
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Short Text
Long Text
No ADS-B Position
AXP322 Lost GPS Position Data
Xpndr Fault
AXP322 Transponder Fault
Comments
ADS-B position data had previously been valid and then transitions to invalid.
Check the ADS-B position source device.
Any fault other than loss of ADS-B GPS position. Contact the Avidyne Service Center if this persists across power cycles.
No Comm With Xpdr
No Communication with Remote Transponder
Radar: Echos Ahead
Radar: Heavy Echos Ahead
Radar: Target Alert Radar: Target Alert Detected
No data has been received from the remote transponder for greater than 2 seconds. Contact the Avidyne Service Center if this persists across power cycles.
Generated when a number of red and/or magenta echos are present within the area ±22q off the nose of the aircraft at the current displayed radar range.
Alerts the pilot to the presence of a significant weather cell that exists beyond the currently selected display range.
Radar Sensor Fault
No Communication with Radar Sensor, or;
Radar Data is Invalid, or;
Sensor mode is [selected] Selected mode is [reported], or;
Radar fault code: any active fault codes.
No data is received from the sensor for at least 2 seconds, or;
The data stream from the radar contains information that the data stream should not be used, or;
If the requested mode and the reported mode do not match, or;
Any specific fault code is active from the sensor.
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Short Text
Long Text
TIS Removed
TIS Traffic Removed
TIS Unavailable
TIS Traffic Unavailable
Too Low, Terrain Sink Rate
Premature Descent, below glide path
Excessive Descent Rate
Don't Sink TAWS Fail
Negative climb rate or altitude loss
Invalid GPS Positon/Velocity
TAWS System Failure
TAWS Failed Self-Test [reason why]
Comments
TIS traffic communications have ceased for >12 seconds No TIS ground station is available or communications have ceased for >60 seconds TAWS PDA algorithm has determined the aircraft is below glide path. TAWS EDR algorithm has determined a potential CFIT scenario is developing recover the aircraft TAWS NCR algorithm has determined corrective action should be t aken immediately. The GPS solution is lost or the GPS velocity quality parameters drop below required accuracy limits. A "bing-bong" chime is played if this condition occurs. Contact the Avidyne Service Center if this persists across power cycles. TAWS failed self-test for the reason provided and TAWS will be degraded or not available for the power cycle. Contact the Avidyne Service Center if this persists across power cycles.
The pilot should utilize available instruments/data displays to verify message(s) and take appropriate action(s) (ref POH/AFM) by selection of alternate systems or settings. Invalid messages generally indicate a failed sensor and that other messages associated with that system will be unavailable. Caution messages indicate the possibility of a pilot action.
FAA APPROVED Date:
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Section 4 Normal Procedures
To Activate the IFD4XX/IFD5XX :
1. Verify IFD circuit breakers (2) ------------------------------ IN 2. Verify Battery Master Switch -------------------------------- ON 3. Avionics or Radio Master (if equipped) ------------------ ON
To Deactivate the IFD4XX/IFD5XX :
4. Avionics or Radio Master (if equipped) ------------------ OFF or
5. Press and hold the Power Knob----------------------------- OFF
IMC Operations with Weather Radar 1. While operating in IMC conditions with weather radar active, activate lightning detection system and monitor. Correlate lightning strike information with painted radar information to confirm proper system operation. 2. In the event that radar data and lightning do not coincide, contact ATC for the latest severe weather information.
Also see Avidyne IFD4XX/IFD5XX Pilot's Guides for Normal operation procedures.
FAA APPROVED Date:
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Section 5 Performance
No change from basic Handbook.
FAA APPROVED Date:
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Section 6 Weight and Balance
No change from basic Handbook. See AFM/POH for current weight and balance for this aircraft.
FAA APPROVED Date:
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Section 7 Systems Description
See Avidyne IFD4XX and IFD5XX FMS/GPS/Nav/Com Pilot Guides
P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800 P/N 600-00317-000 for the IFD545 and IFD550 P/N 600-00318-000 for the IFD510 P/N 600-00319-000 for the IFD410
FAA APPROVED Date:
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EASA Approved Airplane Flight Manual Supplement
For _________________________________
Make and Model Airplane
with Avidyne Integrated Flight Displays p/n 700-00182-XXX
and 700-00179-XXX
Registration No. _________
Serial No. __________
This supplement must be attached to the applicable FAA Approved Airplane Flight Manual when Avidyne 700-00182-XXX Integrated Flight Display (IFD) and/or 700-00179-XXX Integrated Flight Display installed in accordance with EASA STC 10058132. The information contained herein supplements or supersedes the basic manual only in those areas listed. For limitations and procedures not contained in this supplement consult the basic Airplane Flight Manual.
FAA Approved on behalf of the European Aviation Safety Agency (EASA): __________________________________
Digitally signed by WILLIAM P
WILLIAM P WITZIG WITZIG Date: 2019.05.03 14:33:00 -04'00' 0DQDJHU1RUWKHDVW)OLJKW7HVW6HFWLRQ )HGHUDO$YLDWLRQ$GPLQLVWUDWLRQ %XUOLQJWRQ0$
EASA Approval Number: _________________
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P/N 600-00298-001 Rev 03
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LOG OF REVISIONS
Revision Number
Revised Pages
00
ALL
3, 4, 5, 8, 9, 10, 17, 18, 22
01
1, 2, 3, 5, 6, 8, 9, 12, 17, 02 23
03
5, 24
Description of Revisions
Initial Release
Add IFD 410, IFD 510 models. Address new limitations and messages associated with software release 10.2 Add IFD 545, IFD 550 models, add new limitations and messages associated BK pilot guide references
EASA Approval
Yves Morier
N. Faust manager Boston ACO FAA on behalf of EASA
Date
17 May 2016
06 April 2017
W Witzig AIR711 FAA on Behalf of EASA
16 August 2017
::LW]LJ)$$$,5IRU ($6$
A vertical black line in the margin shows revised portions of affected pages.
EASA Approval Number: _________________
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Section 1 General
This airplane is equipped with an Avidyne p/n 700-00182-XXX IFD5XX Integrated Flight Display (IFD) and /or Avidyne p/n 70000179-XXX IFD4XX Integrated Flight Display. Both part numbers may be referred to in this document as simply IFD.
The IFD contains a GPS (SBAS) receiver (all IFD models), VHF Nav/Com transceiver (IFD440, IFD540 and IFD550) and processing to accomplish control, display, navigation and input/output to other avionic systems. The IFD 545 and IFD550 include an internal ARS and are capable of displaying attitude information and ego-centric synthetic vision (SVS). All IFD models can be configured for Bluetooth and WiFi in/out communication (optional).
The information in the supplement is EASA approved material and must be attached to the EASA Approved Airplane Flight Manual, when the airplane has been modified by the installation of an Avidyne Integrated Flight Display (IFD) in accordance with STC 10058132.
The Avidyne Integrated Flight Displays (IFD) complies with the equipment requirements for P-RNAV and BRNAV/RNAV-5 operations in accordance with AC 90-96A CHG 1. This does not constitute an operational approval.
Within Europe, RAIM availability can be determined using the AUGER GPS RAIM Prediction Tool at http://augur.ecacnav.com/augur/app/home.
1.2 Reference Materials
Temporary Guidance leaflet (TGL) 10 Rev 1 Airworthiness and Operational Approval for Precision RNAV Operations in Designated European Airspace.
Acceptable Means of Compliance 20-27 Airworthiness Approval and Operational Criteria for RNP APPROACH (RNP APCH) Operations including APV BARO-VNAV Operations
EASA Approval Number: _________________
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Acceptable Means of Compliance 20-28 Airworthiness Approval and Operational Criteria for RNAV GNSS Approach Operations to LPV Minima using SBAS
Acceptable Means of Compliance 20-4 Airworthiness Approval and Operational Criteria for the use of Navigation Systems in European Airspace Designated for Basic RNAV Operations (BRNAV)
1.3 Database Accuracy and Completeness
The operator is responsible to ensure that the navigation data used in the unit has the accuracy, resolution, and timeliness appropriate for the purpose of the flight operation being conducted. Using navigation data from an Avidyne authorized supplier will ensure that the navigation data has the same accuracy and resolution provided by official sources, in a format compatible with the intended function of the unit.
Avidyne requests that any observed database discrepancies are reported. These discrepancies may be in the form of an incorrect procedure, incorrectly identified terrain, obstacles, navigation fixes, or any other displayed item used for navigation or communication in the air or on the ground. Use the Service Hotline listed on the back cover of the IFD4XX and IFD5XX Pilot Guides.
Avidyne accurately processes and validates the database data, but cannot guarantee the accuracy and completeness of the data provided by various state sources and their suppliers.
Avidyne Corporation holds a FAA Type 2 Letter of Acceptance (LOA) in accordance with AC 20-153 for database integrity, quality, and database management practices for the navigation database. Flight crew and operators can view the LOA at www.avidyne.com.
EASA Approval Number: _________________
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Section 2 Limitations
1. The Avidyne IFD4XX and IFD5XX Integrated Flight Display Pilot Guides: P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800 P/N 600-00317-000 for the IFD545 and IFD550 P/N 600-00318-000 for the IFD510 P/N 600-00319-000 for the IFD410 must be available to the pilot during all flight operations.
2. For Class I airplanes (single engine, piston, under 6,000# GTOW), a single IFD540 or IFD440 is required for flight under instrument flight rules (IFR). IFR is prohibited when the GPS or VHF navigation receiver is inoperable.
For all other Airplanes (Class II, III and IV), dual VHF communications transceivers and dual GPS or VHF Navigation receivers are required for flight under instrument flight rules (IFR). One communication transceiver, or one GPS receiver, or one VHF navigation receiver may be inoperable for IFR flight.
In all airplanes, an approved navigation display (external CDI, HSI, or EHSI) is required for flight under instrument flight rules (IFR).
3. WiFi and Bluetooth wireless features may not be used during critical phases of flight to include takeoff, approaches, landing. WiFi and Bluetooth must be selected off on the user setup tab (SYS/Setup) during these phases of flight.
4. Any portable electronic device (PED) that transmits data to IFD4XX/IFD5XX units must be checked and approved prior to use in flight.
EASA Approval Number: _________________
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5. All IFD models are prohibited from use of Bluetooth and WiFi communications features in Class IV airplanes. These features, if not disabled by installation configuration, must be selected off in user setup by the pilot.
6. The IFD4XX and/or IFD5XX installed with an SBAS approved antenna, provides pilot and automatic flight control guidance for the following operations conducted under instrument flight rules (IFR):
Note: That models IFD410, IFD510 and IFD545 do not include VHF capabilities and VHF navigation and approaches are not applicable to these models.
x VOR, LOC, ILS instrument approach procedures (procedures using VHF radio guidance)
x Instrument approach procedures using the following lines of minima: o LNAV minima (including when using advisory vertical guidance from the system); o LNAV/VNAV minima; o LPV minima; o LP minima
x B-RNAV/ RNP-5/RNAV-5, RNP-10, RNP-APCH [titled RNAV (GPS) or RNAV(GNSS)] terminal procedures, including arrival and departure procedures.
x RNP-1/RNAV-1, RNP-2/RNAV-2, RNAV terminal procedures, including RNAV arrival and RNAV departure procedures. P-RNAV, RNAV Routes (DPs, STARS, Q and T Routes)
x Oceanic and Remote Areas of Operation
7. The IFD4XX and/or IFD5XX when installed with a nonSBAS antenna, provide pilot and automatic flight control guidance for the following operations conducted under instrument flight rules (IFR): x VOR, LOC, ILS instrument approach procedures (procedures using VHF radio guidance)
EASA Approval Number: _________________
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x Instrument approach procedures using the following lines of minima: o LNAV minima
x B-RNAV/ RNP-5/RNAV-5, RNP-10, RNP-APCH [titled RNAV (GPS) or RNAV(GNSS)] terminal procedures, including arrival and departure procedures.
x RNP-1/RNAV-1, RNP-2/RNAV-2, RNAV terminal procedures, including RNAV arrival and RNAV departure procedures. P-RNAV, RNAV Routes (DPs, STARS, Q and T Routes)
x Oceanic and Remote Areas of Operation
8. GPS/SBAS based IFR enroute, oceanic, and terminal navigation is prohibited unless a current navigation database is installed.
9. Use of RNP terminal operations and RNP instrument approach procedures containing RF leg segments (identified on the approach plate) is prohibited.
10. In areas where SBAS coverage is not available, the pilot must check RAIM availability.
11. The Avidyne moving map display provides visual depiction of the aircraft's own-ship, GPS position on a moving map for situation awareness (SA) purposes only. The pilot shall not use the moving map display as a sole means of navigation. The external CDI, HSI, or EHSI display must be used as the primary navigation instrument.
12. The Avidyne electronic checklists are not EASA approved and may not be loaded or used. Use of this feature will require further certification and operational approval.
13. The IFD integrates with separately approved system installations such navigation indicators, remote annunciators, weather, traffic and terrain alerting systems. Adherence to limitations in installation AFM supplements for those systems is mandatory.
14. The use of datalink, traffic and lightning sensor information
displayed on the IFD4XX and IFD5XX must be in
EASA Approval Number:
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compliance with the approved AFM supplements for those systems.
15. Gloves may not be used to operate the IFD4XX and IFD5XX touch functions unless the Glove Qualification Procedure located in the respective IFD Pilot's Guides, has been successfully completed.
16. For flight planning purposes, in areas where SBAS coverage is not available, the flight crew must check RAIM availability.
In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended route of flight, the flight shall be delayed, canceled, or rerouted on a track where RAIM requirements can be met. The flight may also be re-planned using non-GPS based navigational capabilities.
For flight planning purposes for operations within European B-RNAV/RNAV-5 and P-RNAV airspace, if more than one satellite is scheduled to be out of service, then the availability of GPS RAIM shall be confirmed for the intended flight (route and time). In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended flight, the flight shall be delayed, canceled, or rerouted on a track where RAIM requirements can be met.
NOTE
Within Europe, RAIM availability can be determined using Europe's AUGER GPS RAIM Prediction Tool at http://augur.ecacnav.com/augur/app/home.
17. Coupling to an installed autopilot that is not identified as an approved, compatible autopilot in the approved installation manual for AML STC 10058132 is not authorized.
18. The Avidyne IFD4XX and IFD5XX Terrain Alerting (TA) and Forward Looking Terrain Alerting (FLTA) non-TSO'd features are to be used for improved terrain/obstacle
EASA Approval Number: _________________
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awareness and do not meet TAWS-B requirements for specific operations.
CAUTION
Terrain information shown on the MAP page display is provided to the pilot as an aid to situational awareness. The MAP page terrain color representations should not be used as a sole basis for terrain avoidance.
CAUTION
Traffic information shown on the Map page display is provided to the pilot as an aid to visually acquiring traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic. Avoidance maneuvers should not be made based only on a Traffic Advisory.
19. For CS23 Class IV airplanes the IFD545 and IFD550 may not be used for primary attitude information or standby attitude information (If required by type design). The IFD545 and/or IFD550 may only be used as a secondary (non-required) source for attitude information.
NOTE
The IFD545 and/or IFD550 may be used in conjunction with air data and turn rate indicators in determining if a primary or standby attitude source has failed e.g. in the case of primary/standby attitude indicator mis-compare.
20. The IFD545 and/or IFD550 may not be used for primary navigation deviation information (horizontal of vertical). The IFD545 and/or IFD550 may only be used as a secondary (non-required) source for this information.
EASA Approval Number: _________________
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21. The Avidyne IFD4XX and IFD5XX may only be operated in IMC conditions as a radar display when used in conjunction with an independent lightning detection and display system (Approved Thunderstorm Detection Equipment).
CAUTION
Terrain information shown on the MAP page display is provided to the pilot as an aid to situational awareness. The MAP page terrain color representations should not be used as a sole basis for terrain avoidance.
CAUTION
Traffic information shown on the Map page display is provided to the pilot as an aid to visually acquiring traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic. Avoidance maneuvers should not be made based only on a Traffic Advisory.
CAUTION
In IFD545 and IFD550 units the inertial reference accelerometers may be irreparably damaged by exposure to temperatures below -40°C. The units are capable of operating at -40°C, but exposure to temperatures below this, even when powered off, can stress the parts internally causing a detectable and annunciated failure of the sensors.
EASA Approval Number: _________________
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Section 3 Emergency Procedures
Loss of GPS
In the event of the loss of the IFD4XX or IFD5XX GPS receiver, the FMS will enter dead reckoning mode for 5 minutes, after that all FMS functions are lost and the ownship is removed from map depictions. The pilot should revert to remaining navigation receiver (required for IFR operations).
Loss of VHF Nav/Com
In the event of the loss of IFD4XX or IFD5XX VHF navigation, the pilot should revert to remaining navigation receiver (required for IFR operations).
Warning Messages
Caution and warning messages provided by the IFD4XX and IFD5XX are related to functions performed by the IFD4XX and IFD5XX and are additional to the caution and warning annunciation system provided by the aircraft.
NOTE The original caution and warning annunciator panel remains as the primary indication. POH/AFM Emergency procedures are not affected by this installation.
EASA Approval Number: _________________
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Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Caution and Warning Messages
The Caution and Warning panel is not altered as part of this modification and remains the primary means of providing Caution and Warning messages.
Caution and Warning messages are provided in the following table:
EXCEEDANCES | WARNINGS RED
Short Text
Long Text
Terrain Pull-Up* Terrain Pull-Up
Warning Obstacle*
Warning Obstacle
Unit Overtemp Unit Unreliable
Unit Overtemp: <internal component name> Unit reliability in question Get IFD serviced
Low Volts off in <countdown from 60> sec
Pull Up
Low Volts IFD powers down in <countdown from 60> sec
Excessive Descent Rate
Comments
The FLTA algorithm has detected an imminent ground collision Initiate an immediate recovery maneuver.
The FLTA algorithm has detected an imminent obstacle collision.
Initiate an immediate recovery maneuver.
One or more of the internal components has exceeded its maximum design temperature and reliability cannot be ensured until the unit is tested by the Avidyne Service Center.
Contact the Avidyne Service Center or a local dealer for service. This message will be present on every subsequent power cycle until reset by the Avidyne Service Center.
Main supply voltage has fallen below 9 VDC. Contact a local dealer for service.
The TAWS Excessive Descent Rate algorithm has detected a CFIT potential initiate an immediate recovery maneuver.
EASA Approval Number: _________________
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Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 EXCEEDANCES | CAUTIONS YELLOW
Short Text Caution Terrain*
Long Text Caution Terrain
Caution Obstacle* Caution Obstacle
GPS Integrity Lost
GPS Integrity Lost Crosscheck Nav
GPS Fault Dead Reckoning
Position updated via dead reckoning
Comments
The FLTA algorithm is predicting a likely ground collision within approximately 60 seconds initiate a proper recovery maneuver.
The FLTA algorithm is predicting a likely obstacle collision with approximately 60 seconds initiate a proper recovery maneuver.
This is alerting about imminent exceedence of horizontal fault detection limits or protection levels.
Crosscheck the nav solution and determine the best course of action.
If on a GPS based approach, Missed Approach is required.
The system will use the last known position and groundspeed (and heading if available) to estimate the aircraft position following loss of GPS for up to 5 minutes. Since Dead Reckoning assumes no directional or groundspeed change, it will not be reliable even during those first 5 minutes if either or both of these factors have changed.
Execute a missed approach if this occurs while performing a GPS based approach. Use an alternate GPS or VHF navigation receiver.
EASA Approval Number: _________________
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Short Text
Long Text
GPS Fault No
No position available
Position
Configuration Error
Configuration Error IFD Requires Service
LPV Unavailable Use L/VNAV DA
GPS integrity is insufficient for LPV Approach
LPV Unavailable Use LNAV MDA
GPS integrity is insufficient for LPV Approach
LP Unavailable Use LNAV MDA
L/VNAV Unavail. Use LNAV MDA
VNAV Lost Use LNAV MDA
GPS integrity is insufficient for LP Approach
GPS integrity is insufficient for L/VNAV Approach
Excessive XTK or Low GPS Integrity for Vertical Guidance
Comments
The navigation solution cannot compute a position, typically after dead reckoning has expired. .
Execute a missed approach if this occurs while performing a GPS based approach. Use an alternate GPS or VHF navigation receiver.
The configuration of the IFD or the devices to which it is communicating with has changed or experienced an error.
Contact the Avidyne Service Center or a local dealer for service.
Transition to a non-LPV approach and the appropriate minima if possible. Otherwise execute a missed approach.
Transition to a non-LPV approach and the appropriate minima if possible. Otherwise execute a missed approach.
Transition to a non-LP approach and the appropriate minima.
Transition to a non-L/VNAV approach and the appropriate minima.
Transition to LNAV minima.
EASA Approval Number: _________________
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Short Text
Long Text
Check Altitude Too Low
Aircraft is below the glide slope altitude at FAF
Comments
Correct aircraft altitude as required to safely conduct the approach or initiate a climb to a published safe altitude and abort the approach.
Traffic Sensor Fault*
Traffic <Low | High> <Bearing in clock direction> <Distance in NM>*
Traffic <Low | High> <Distance in NM>*
No communication with traffic sensor (local) OR Traffic sensor has failed (global) Traffic [Brg (e.g. 1:00)] [dist (e.g. 2 NM)] [alt (e.g. 200 ft)]
Traffic <Distance in NM> <Signed relative altitude in feet> FT
Contact a local dealer for service.
Traffic advisories - Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic. Traffic advisories with no bearing information Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
EASA Approval Number: _________________
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Short Text
Long Text
Traffic <Bearing in clock direction> <distance in NM>*
Traffic <bearing in clock direction> <distance in NM>
Traffic <distance in NM>*
Traffic <distance in NM>
Comments
Traffic advisories with no relative altitude information Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Traffic advisories with no relative altitude information and no bearing Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
COM TX Fault COM Stuck TX
Transmitter Fault, No TX Ability
Stuck Mic Timeout, Transmitter Disabled
Transition to a backup VHF com radio (if available) or initiate lost communication procedures. Contact the Avidyne Service Center or a dealer for service.
Requires 35 seconds of continuous transmission. Verify the PTT is stuck and contact a dealer for service as required.
EASA Approval Number: _________________
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Short Text
Long Text
No Comm with VHF No communication with the VHF radio
Unit Overtemp Check cooling
Unit Overtemp: <internal component identification>
Comments
Transition to a backup VHF com radio (if available) or initiate lost communication procedures. Contact the Avidyne Service Center or a dealer for service.
One or more of the internal components has exceeded 80qC. Contact the Avidyne Service Center or a dealer for service consider adding a source of cooling and/or improving air flow in/around the IFD.
Low Volts
Backlight reduced to 25%
Main supply voltage has fallen to approximately 11VDC.
Check the aircraft alternators are on and functional.
Consider load shedding the power bus that is powering the IFD.
Manual Sequence Req'd
Heading Lost
Altitude invalid leg will not auto sequence
Using ground track for SVS
In basic E-M aircraft where the IFD does not have altitude input, this message will appear when the FMS active leg is a HeadingÆAltitude leg. In this case, the FMS flight plan will need to be manually sequenced to the next leg. Failure to do so will keep the FMS flying the heading indefinitely.
Indicates loss of the TVV and the aircraft reference symbol ("wedge") now points at ground track, not aircraft heading. "TRK" will also be displayed below the digital compass on the SVS page.
EASA Approval Number: _________________
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Short Text
Long Text
No ADS-B Position (s/w 10.1 or later)
AXP322 Lost GPS Position Data
Xpndr Fault (s/w 10.1 or later)
AXP322 Transponder Fault
No Comm With Xpdr
(s/w 10.1 or later)
No Communication with Remote Transponder
Radar: Echos Ahead
Radar: Heavy Echos Ahead
Radar: Target Alert Radar: Target Alert Detected
Comments
ADS-B position data had previously been valid and then transitions to invalid.
Check the ADS-B position source device.
Any fault other than loss of ADS-B GPS position. Contact the Avidyne Service Center if this persists across power cycles.
No data has been received from the remote transponder for greater than 2 seconds. Contact the Avidyne Service Center if this persists across power cycles.
Generated when a number of red and/or magenta echos are present within the area ±22q off the nose of the aircraft at the current displayed radar range.
Alerts the pilot to the presence of a significant weather cell that exists beyond the currently selected display range.
Radar Sensor Fault
No Communication with Radar Sensor, or;
Radar Data is Invalid, or;
Sensor mode is [selected] Selected mode is [reported], or; Radar fault code: any active fault codes.
No data is received from the sensor for at least 2 seconds, or;
The data stream from the radar contains information that the data stream should not be used, or;
If the requested mode and the reported mode do not match, or;
Any specific fault code is active from the sensor.
TIS Removed
TIS Traffic Removed
TIS traffic communications have ceased for >12 seconds
EASA Approval Number: _________________
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Short Text
Long Text
TIS Unavailable
TIS Traffic Unavailable
Too Low, Terrain Sink Rate
Premature Descent, below glide path
Excessive Descent Rate
Don't Sink TAWS Fail
Negative climb rate or altitude loss
Invalid GPS Position/Velocity
TAWS System Failure
TAWS Failed Self-Test [reason why]
Comments
No TIS ground station is available or communications have ceased for >60 seconds TAWS PDA algorithm has determined the aircraft is below glide path. TAWS EDR algorithm has determined a potential CFIT scenario is developing recover the aircraft TAWS NCR algorithm has determined corrective action should be taken immediately. The GPS solution is lost or the GPS velocity quality parameters drop below required accuracy limits. A "bing-bong" chime is played if this condition occurs. Contact the Avidyne Service Center if this persists across power cycles. TAWS failed self-test for the reason provided and TAWS will be degraded or not available for the power cycle. Contact the Avidyne Service Center if this persists across power cycles.
The pilot should utilize available instruments/data displays to verify message(s) and take appropriate action(s) (ref POH/AFM) by selection of alternate systems or settings. Invalid messages generally indicate a failed sensor and that other messages associated with that system will be unavailable. Caution messages indicate the possibility of a pilot action.
EASA Approval Number: _________________
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Section 4 Normal Procedures
To Activate the IFD4XX/IFD5XX :
1. Verify IFD circuit breakers (2) ------------------------------ IN 2. Verify Battery Master Switch --------------------------------ON 3. Avionics or Radio Master (if equipped) ------------------ ON
To Deactivate the IFD4XX/IFD5XX :
1. Avionics or Radio Master (if equipped) ------------------ OFF or
2. Press and hold the Power Knob----------------------------- OFF
Autopilots
Reference autopilot Pilots Guide and AFMS.
The IFD4XX/IFD5XX may be coupled to an autopilot. Autopilots coupled to the IFD4XX/IFD5XX in (NAV) mode will follow GPS or VHF navigation guidance as they would with any VOR/LOC receiver. Autopilots providing GPSS (GPS Roll Steering) course guidance will lead course changes (curved transition), fly arcs, holds and procedure turn/reversals.
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Section 5 Performance
No change from basic Handbook.
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Section 6 Weight and Balance
No change from basic Handbook. See POH for current weight and balance for this aircraft.
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Section 7 Systems Description
See Avidyne IFD4XX and IFD5XX FMS/GPS/Nav/Com Pilot Guides
P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800 P/N 600-00317-000 for the IFD545 and IFD550 P/N 600-00318-000 for the IFD510 P/N 600-00319-000 for the IFD410
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FAA Approved Airplane Flight Manual Supplement
For _________________________________
Make and Model Airplane
with Avidyne Integrated Flight Displays p/n 700-00182-XXX and 700-00179-XXX installed with Collins ProLine 21 Avionics
Registration No. _________
Serial No. __________
This supplement must be attached to the applicable FAA Approved
Airplane Flight Manual when Avidyne 700-00182-XXX Integrated Flight Display and/or 700-00179-XXX Integrated Flight Display (Release 10.2.2 or later approved version) installed in accordance with STC SA00343BO. The information contained herein supplements or supersedes the basic manual only in those areas listed. For limitations and procedures not contained in this supplement consult the basic Airplane Flight Manual.
WILLIAM P
Digitally signed by WILLIAM P
WITZIG
FAA Approved _W__I_T_Z_I_G___________D_at_e:_20_19_.0_5._03_13_:2_6:_35_-0_4'_00_' _
Manager
Northeast Flight Test Section
Federal Aviation Administration
Burlington, MA
FAA Approved: 5/3/2019
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LOG OF REVISIONS
Revision Number
00 01
Revised Pages ALL
4, 5, 8, 27
Description of Revisions
Initial Release
Add Configurations
FAA Approval
Date
WP Witzig
6/18/18
Added TDR ADSB out compliance
statement, BK pilot guide references
::LW]LJ
A vertical black line in the margin shows revised portions of affected pages.
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Section 1 General
This airplane is equipped with an Avidyne p/n 700-00182-XXX IFD5XX Integrated Flight Display and /or Avidyne p/n 700-00179XXX IFD4XX Integrated Flight Display. Both Integrated Flight Display part numbers may be referred to in this document as simply IFD.
The IFD contains a GPS (SBAS) receiver (all IFD models), VHF Nav/Com transceiver (IFD440, IFD540 and IFD550) and processing to accomplish control, display, navigation and input/output to other avionic systems. The IFD 545 and IFD550 include an internal ARS and are capable of displaying attitude information and ego-centric synthetic vision (SVS).
GPS/SBAS TSO-C146c Class 3 Operation The IFD4XX and IFD5XX has airworthiness approval for navigation using GPS and SBAS (Satellite Based Augmentation System complying with ICAO Annex 10) for IFR en route, terminal area, and non-precision approach operations ("GPS", "or GPS", and "RNAV (GPS)" approaches). The IFD4XX and IFD5XX are approved for approach procedures with vertical guidance including "LPV" and "LNAV/VNAV" and approaches without vertical guidance including "LP" and "LNAV".
The IFD4XX and IFD5XX comply with the requirements for GPS Class II oceanic and remote navigation (RNP-10) and (RNP-4) without time limitations. A second navigation source may be required for these operations to meet availability requirements.
NOTE
The IFD4XX and IFD5XX must be at software Release 10.2.2 or later approved version to be capable of GPS precision approaches with vertical guidance when installed with ProLine 21 Avionics.
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Database Accuracy and Completeness The operator is responsible to ensure that the navigation data used in the unit has the accuracy, resolution, and timeliness appropriate for the purpose of the flight operation being conducted. Using navigation data from an Avidyne authorized supplier will ensure that the navigation data has the same accuracy and resolution provided by official sources, in a format compatible with the intended function of the unit.
Avidyne requests that any observed database discrepancies are reported. These discrepancies may be in the form of an incorrect procedure, incorrectly identified terrain, obstacles, navigation fixes, or any other displayed item used for navigation or communication in the air or on the ground. Use the Service Hotline listed on the back cover of the IFD4XX and IFD5XX Pilot Guides.
Avidyne accurately processes and validates the database data, but cannot guarantee the accuracy and completeness of the data provided by various state sources and their suppliers.
Avidyne Corporation holds a FAA Type 2 Letter of Acceptance (LOA) in accordance with AC 20-153 for database integrity, quality, and database management practices for the navigation database. Flight crew and operators can view the LOA at www.avidyne.com.
ADS-B OUT Compliance The IFD4XX and/or IFD5XX installed per this STC in conjunction with the following transponders/ UAT transceivers have been shown to meet the equipment requirements of 14 CFR 91.227 for ADS-B OUT:
Garmin GTX330ES Garmin GTX335/345 Collins TDR94(D)
IFD4XX and IFD5XX have been approved for ADS-B Out compliance with other transponders under separate installation approvals (STCs). Check the aircraft's transponder or UAT transceiver AFMS for the statement above indicating ADS-B out compliance for the navigator and transmitter combination.
FAA Approved: 5/3/2019
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ADS-B In Only The IFD4XX and/or IFD5XX installed per this STC may be interfaced with an ADS-B UAT or 1090MHz receiver (ADS-B In) that does not provide ADS-B out capability. If no ADS-B out system is installed, this installation will not be able to receive TIS-B client status, and will not receive ADS-R or TIS-B broadcasts from ATC unless the aircraft is in the same area as a valid TIS-B client broadcasting that it has ADS-B In capability.
Figure 1. Avidyne IFD540 700-00182-XXX Integrated Flight Display (IFD).
USB Port
Volume / Power /
CDI Nav Source Frequency
Ambient Light
Line Select Keys
Com/Nav Manual Tuning
Camera/Latc h
Page Function
FAA Approved: 5/3/2019
Dedicated Function
Context Sensitive IFD
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Figure 2. Avidyne IFD440 700-00179-XXX Integrated Flight Display (IFD).
Volume / Power / Squelch Knob
Frequency Swap
Line Select Keys (LSKs)
CDI Nav Source Knob
Ambient Light Sensor
Dedicated Function Keys
Cam Latch
Com/Nav Manual Tuning Knob
Page Function Keys
USB Port
Context Sensitive IFD Knob
FAA Approved: 5/3/2019
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Figure 3. Avidyne IFD550 700-00182-XXX Integrated Flight Display Ego-centric SVS.
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Section 2 Limitations
1. The Avidyne IFD4XX and IFD5XX Integrated Flight Display Pilot Guides: P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800 P/N 600-00317-000 for the IFD545 and IFD550 P/N 600-00318-000 for the IFD510 P/N 600-00319-000 for the IFD410 must be available to the pilot during all flight operations.
In all airplanes, the approved navigation display (external CDI, HSI, or EHSI) is required for flight under instrument flight rules (IFR).
2. To display GPS approaches with vertical guidance from an IFD4XX/IFD5XX on the Pro Line 21 Primary Flight Display (PFD), VLOC1/2 must be selected once established inbound on the final approach course. A separate annunciator indicating GPS as the active navigation source selection is required in the pilot's primary field of view.
3. The IFD4XX and/or IFD5XX installed with an SBAS approved antenna, provides pilot and automatic flight control guidance for the following operations conducted under instrument flight rules (IFR): x VOR, LOC, ILS instrument approach procedures (procedures using VHF radio guidance) IFD440, IFD540, IFD550 only x RNP instrument approach procedures using the following lines of minima: o LNAV minima (including when using advisory vertical guidance from the system); o LNAV/VNAV minima; o LPV minima; and o LP minima.
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Note: The U.S. titles RNP instrument approach procedures "RNAV (GPS) Rwy XX". Other States may use similar titling or may title these procedures "RNAV (GNSS) Rwy XX". x RNP terminal procedures, including RNP arrival procedures and RNP departure procedures. x RNAV terminal procedures, including RNAV arrival procedures and RNAV departure procedures.
The IFD4XX and/or IFD5XX when installed with a nonSBAS antenna, provide pilot and automatic flight control guidance for the following operations conducted under instrument flight rules (IFR): x VOR, LOC, ILS procedures (procedures using VHF
radio guidance) IFD440, IFD540, IFD550 only; x RNP instrument approach procedures using the
following lines of minima: o LNAV minima.
x RNP terminal procedures, including RNP arrival procedures and RNP departure procedures.
x RNAV terminal procedures, including RNAV arrival procedures and RNAV departure procedures.
4. When GPS is available, the IFD440 and/or IFD540/550 , may serve as an RNAV alternate or substitute means of navigation for ground-based navigation aids that are out-ofservice or unavailable.
5. GPS/SBAS based IFR enroute, oceanic, and terminal navigation is prohibited unless current Navigation and Procedure databases are installed.
6. Use of RNP terminal operations and RNP instrument approach procedures containing RF leg segments (identified on the approach plate) is prohibited.
7. In areas where SBAS coverage is not available, the pilot must check RAIM availability.
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8. The Avidyne moving map display provides visual depiction of the aircraft's own-ship, GPS position on a moving map for situational awareness (SA) purposes only. The pilot
shall not use the moving map display as a sole means of navigation. The external CDI, HSI, or EHSI display must be used as the primary navigation instrument.
9. The Avidyne electronic checklists display supplements the Pilot Operating Handbook checklists and are advisory only. The pilot shall not use the electronic checklists as the primary set of on-board aircraft checklists. FAA Approved Flight Manual paper checklist must be available to the pilot as the primary reference.
10. The IFD integrates with separately approved system installations such navigation indicators, remote annunciators. Adherence to limitations in installation AFM supplements for those systems is mandatory.
11. The use of datalink, traffic and lightning sensor information displayed on the IFD4XX and IFD5XX must be in compliance with the approved AFM supplements for those systems.
12. Gloves may not be used to operate the IFD4XX and IFD5XX touch functions unless the Glove Qualification Procedure located in the IFD4XX/IFD5XX Pilot's Guides has been successfully completed.
13. The IFD545 and IFD550 may not be used for primary attitude information or standby attitude information (If required by type design). The IFD545 and/or IFD550 may only be used as a secondary (non-required) source for attitude information.
NOTE
The IFD545 and/or IFD550 may be used in conjunction
with air data and turn rate indicators in determining if a
primary or standby attitude source has failed e.g. in the case
of primary/standby attitude indicator mis-compare.
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14. The IFD545 and/or IFD550 may not be used for primary navigation deviation information (horizontal or vertical). The IFD545 and/or IFD550 may only be used as a secondary (non-required) source for this information.
15. The Avidyne IFD4XX and IFD5XX may only be operated in IMC conditions as a radar display when used in conjunction with an independent lightning detection and display system (Approved Thunderstorm Detection Equipment).
CAUTION
Terrain information shown on the MAP page display is provided to the pilot as an aid to situational awareness. The MAP page terrain color representations should not be used as a sole basis for terrain avoidance.
CAUTION
Traffic information shown on the Map page display is provided to the pilot as an aid to visually acquiring traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic. Avoidance maneuvers should not be made based only on a Traffic Advisory.
CAUTION
In IFD545 and IFD550 units the inertial reference accelerometers may be irreparably damaged by exposure to temperatures below -40°C. The units are capable of operating at -40°C, but exposure to temperatures below this, even when powered off, can stress the parts internally causing a detectable and annunciated failure of the sensors.
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Placards
The following is required to be affixed adjacent to the left and right Primary Flight Displays. Placard font must be at least 3/16" of contrasting color and easily legible from the crew positions.
To display GPS approaches with vertical guidance from an IFD4XX/IFD5XX
Navigator, VLOC1 must be selected on the Primary Flight Display once established inbound on the final approach course.
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Section 3 Emergency Procedures
Loss of GPS In the event of the loss of the IFD440 or IFD540 GPS receiver, the FMS will enter dead reckoning mode for 5 minutes, after that all FMS functions are lost and the ownship is removed from map depictions. The pilot should revert to remaining navigation receiver (required for IFR operations).
Loss of VHF Nav/Com In the event of the loss of IFD440, IFD540 or IFD550 VHF navigation, the pilot should revert to remaining navigation receiver (required for IFR operations).
Warning Messages Caution and warning messages provided by the IFD4XX and IFD5XX are related to functions performed by the IFD4XX and IFD5XX and are additional to the caution and warning annunciation system provided by the aircraft.
NOTE
The original caution and warning annunciator panel remains as the primary indication. POH/AFM Emergency procedures are not affected by this installation.
CAUTION
IFD4XX units lack an audio inhibit output to preclude other sensors aural alerts from sounding while IFD4XX forward looking terrain awareness (FLTA) aural alerts are issued. Simultaneous alerts are possible. Example; a TIS-B aural traffic alert could be issued at the same time as an FLTA terrain or obstacle aural caution or warning.
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To Disable WiFi/Bluetooth Connectivity on IFD4XX/IFD5XX: 1. Press and hold the IFD4xx/IFD5XX power button/knob for 1 second (upper left bezel) -------------------------------------2. ALLOW/IGNORE WiFi Bluetooth dropdown is presented. Press IGNORE--------------------------- Dropdown is removed 3. Verify the WiFi and Bluetooth icons on the upper right of the display are removed--------------------- Extinguish
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Caution Messages The Caution and Warning panel is not altered as part of this modification and remains the primary means of providing Caution and Warning messages.
Caution and Warning messages are provided in the following table:
EXCEEDANCES | WARNINGS RED
Short Text
Long Text
Terrain Pull-Up* Terrain Pull-Up
Warning Obstacle*
Warning Obstacle
Unit Overtemp Unit Unreliable
Unit Overtemp: <internal component name> Unit reliability in question Get IFD serviced
Low Volts off in <countdown from 60> sec
Pull Up
Low Volts IFD powers down in <countdown from 60> sec
Excessive Descent Rate
Comments
The FLTA algorithm has detected an imminent ground collision Initiate an immediate recovery maneuver.
The FLTA algorithm has detected an imminent obstacle collision.
Initiate an immediate recovery maneuver.
One or more of the internal components has exceeded its maximum design temperature and reliability cannot be ensured until the unit is tested by the Avidyne Service Center.
Contact the Avidyne Service Center or a local dealer for service. This message will be present on every subsequent power cycle until reset by the Avidyne Service Center.
Main supply voltage has fallen below 9 VDC. Contact a local dealer for service.
The TAWS Excessive Descent Rate algorithm has detected a CFIT potential initiate an immediate recovery maneuver.
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EXCEEDANCES | CAUTIONS YELLOW
Short Text Caution Terrain*
Long Text Caution Terrain
Caution Obstacle* Caution Obstacle
GPS Integrity Lost
GPS Integrity Lost Crosscheck Nav
GPS Fault Dead Reckoning
Position updated via dead reckoning
Comments
The FLTA algorithm is predicting a likely ground collision within approximately 60 seconds initiate a proper recovery maneuver.
The FLTA algorithm is predicting a likely obstacle collision with approximately 60 seconds initiate a proper recovery maneuver.
This is alerting about imminent exceedence of horizontal fault detection limits or protection levels.
Crosscheck the nav solution and determine the best course of action.
If on a GPS based approach, Missed Approach is required.
The system will use the last known position and groundspeed (and heading if available) to estimate the aircraft position following loss of GPS for up to 5 minutes. Since Dead Reckoning assumes no directional or groundspeed change, it will not be reliable even during those first 5 minutes if either or both of these factors have changed.
Execute a missed approach if this occurs while performing a GPS based approach. Use an alternate GPS or VHF navigation receiver.
FAA Approved: 5/3/2019
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Short Text GPS Fault No Position
Configuration Error
LPV Unavailable Use L/VNAV DA
LPV Unavailable Use LNAV MDA
LP Unavailable Use LNAV MDA L/VNAV Unavail. Use LNAV MDA VNAV Lost Use LNAV MDA
Long Text No position available
Configuration Error IFD Requires Service
GPS integrity is insufficient for LPV Approach
GPS integrity is insufficient for LPV Approach
GPS integrity is insufficient for LP Approach GPS integrity is insufficient for L/VNAV Approach Excessive XTK or Low GPS Integrity for Vertical Guidance
Comments
The navigation solution cannot compute a position, typically after dead reckoning has expired.
Execute a missed approach if this occurs while performing a GPS based approach. Use an alternate GPS or VHF navigation receiver.
The configuration of the IFD or the devices to which it is communicating with has changed or experienced an error.
Contact the Avidyne Service Center or a local dealer for service.
Transition to a non-LPV approach and the appropriate minima if possible. Otherwise execute a missed approach.
Transition to a non-LPV approach and the appropriate minima if possible. Otherwise execute a missed approach.
Transition to a non-LP approach and the appropriate minima.
Transition to a non-L/VNAV approach and the appropriate minima.
Transition to LNAV minima.
FAA Approved: 5/3/2019
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Short Text
Check Altitude Too Low
Long Text
Aircraft is below the glide slope altitude at FAF
Comments
Correct aircraft altitude as required to safely conduct the approach or initiate a climb to a published safe altitude and abort the approach.
Traffic Sensor Fault*
Traffic <Low | High> <Bearing in clock direction> <Distance in NM>*
No communication with traffic sensor (local) OR
Traffic sensor has failed (global)
Traffic [Brg (e.g. 1:00)] [dist (e.g. 2 NM)] [alt (e.g. 200 ft)]
Traffic <Low | High> <Distance in NM>*
Traffic <Distance in NM> <Signed relative altitude in feet> FT
Contact a local dealer for service.
Traffic advisories - Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Traffic advisories with no bearing information Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
FAA Approved: 5/3/2019
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Short Text Traffic <Bearing in clock direction> <distance in NM>*
Traffic <distance in NM>*
COM TX Fault
COM Stuck TX
Long Text Traffic <bearing in clock direction> <distance in NM>
Traffic <distance in NM>
Transmitter Fault, No TX Ability
Stuck Mic Timeout, Transmitter Disabled
Comments
Traffic advisories with no relative altitude information Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Traffic advisories with no relative altitude information and no bearing Alert to be used to facilitate visual acquisition of traffic. Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
Transition to a backup VHF com radio (if available) or initiate lost communication procedures. Contact the Avidyne Service Center or a dealer for service.
Requires 35 seconds of continuous transmission. Verify the PTT is stuck and contact a dealer for service as required.
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Short Text No Comm with VHF
Unit Overtemp Check cooling
Long Text No communication with the VHF radio
Unit Overtemp: <internal component identification>
Comments
Transition to a backup VHF com radio (if available) or initiate lost communication procedures. Contact the Avidyne Service Center or a dealer for service.
One or more of the internal components has exceeded 80qC. Contact the Avidyne Service Center or a dealer for service consider adding a source of cooling and/or improving air flow in/around the IFD.
Low Volts
Backlight reduced to 25%
Main supply voltage has fallen to approximately 11VDC.
Check the aircraft alternators are on and functional.
Consider load shedding the power bus that is powering the IFD.
Manual Sequence Req'd
Heading Lost
Altitude invalid leg will not auto sequence
Using ground track for SVS
In basic E-M aircraft where the IFD does not have altitude input, this message will appear when the FMS active leg is a HeadingÆAltitude leg. In this case, the FMS flight plan will need to be manually sequenced to the next leg. Failure to do so will keep the FMS flying the heading indefinitely.
Indicates loss of the TVV and the aircraft reference symbol ("wedge") now points at ground track, not aircraft heading. "TRK" will also be displayed below the digital compass on the SVS page.
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Short Text No ADS-B Position
Long Text
AXP322 Lost GPS Position Data
Xpndr Fault
AXP322 Transponder Fault
Comments
ADS-B position data had previously been valid and then transitions to invalid.
Check the ADS-B position source device.
Any fault other than loss of ADS-B GPS position. Contact the Avidyne Service Center if this persists across power cycles.
No Comm With Xpdr
No Communication with Remote Transponder
Radar: Echos Ahead
Radar: Heavy Echos Ahead
Radar: Target Alert Radar: Target Alert Detected
No data has been received from the remote transponder for greater than 2 seconds. Contact the Avidyne Service Center if this persists across power cycles.
Generated when a number of red and/or magenta echos are present within the area ±22q off the nose of the aircraft at the current displayed radar range.
Alerts the pilot to the presence of a significant weather cell that exists beyond the currently selected display range.
Radar Sensor Fault
No Communication with Radar Sensor, or;
Radar Data is Invalid, or;
Sensor mode is [selected] Selected mode is [reported], or;
Radar fault code: any active fault codes.
No data is received from the sensor for at least 2 seconds, or;
The data stream from the radar contains information that the data stream should not be used, or;
If the requested mode and the reported mode do not match, or;
Any specific fault code is active from the sensor.
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Short Text TIS Removed TIS Unavailable Too Low, Terrain Sink Rate
Don't Sink TAWS Fail
TAWS System Failure
Long Text TIS Traffic Removed TIS Traffic Unavailable
Premature Descent, below glide path Excessive Descent Rate
Negative climb rate or altitude loss Invalid GPS Positon/Velocity
TAWS Failed Self-Test [reason why]
Comments
TIS traffic communications have ceased for >12 seconds No TIS ground station is available or communications have ceased for >60 seconds TAWS PDA algorithm has determined the aircraft is below glide path. TAWS EDR algorithm has determined a potential CFIT scenario is developing recover the aircraft TAWS NCR algorithm has determined corrective action should be t aken immediately. The GPS solution is lost or the GPS velocity quality parameters drop below required accuracy limits. A "bing-bong" chime is played if this condition occurs. Contact the Avidyne Service Center if this persists across power cycles. TAWS failed self-test for the reason provided and TAWS will be degraded or not available for the power cycle. Contact the Avidyne Service Center if this persists across power cycles.
The pilot should utilize available instruments/data displays to verify message(s) and take appropriate action(s) (ref POH/AFM) by selection of alternate systems or settings. Invalid messages generally indicate a failed sensor and that other messages associated with that system will be unavailable. Caution messages indicate the possibility of a pilot action.
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Section 4 Normal Procedures
See Avidyne IFD4XX/IFD5XX Pilot's Guides for Normal operation procedures.
To Activate the IFD4XX/IFD5XX :
1. Verify IFD circuit breakers (2) ------------------------------ IN 2. Verify Battery Master Switch -------------------------------- ON 3. Avionics or Radio Master (if equipped) ------------------ ON
To Deactivate the IFD4XX/IFD5XX :
4. Avionics or Radio Master (if equipped) ------------------ OFF or
5. Press and hold the Power Knob----------------------------- OFF
IMC Operations with Weather Radar
1. While operating in IMC conditions with weather radar active, activate lightning detection system and monitor. Correlate lightning strike information with painted radar information to confirm proper system operation.
2. In the event that radar data and lightning do not coincide, contact ATC for the latest severe weather information.
GPS Approach(es) with Vertical Guidance ProLine 21
1. Select FMS1/2 associated with desired IFD4XX/IFD5XX navigator to fly all enroute, transition and initial approach procedure legs.
2. Once established inbound on GPS procedure with vertical guidance, Select VLOC1/2 on the ProLine 21 Primary Flight Display. Adjust course pointer to published inbound course.
3. Verify GPS annunciation on remote annunciator.
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4. Track lateral and vertical guidance on ProLine 21 Primary Nav Indicator per the current published procedure.
5. For missed approach (Published) switch the ProLine 21 Primary Nav Indicator source to FMS1/2 appropriate to the IFD4XX/IFD5XX in use. Verify course is set to active missed approach leg published course.
NOTE When VLOC1/2 is selected on the ProLine 21 Avionics during GPS approaches with vertical guidance, FMS waypoint information is not displayed on the PFD. This information can be selected for display on the IFD5XX/IFD4XX if desired.
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Section 5 Performance
No change from basic Handbook.
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Section 6 Weight and Balance
No change from basic Handbook. See AFM/POH for current weight and balance for this aircraft.
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Section 7 Systems Description
See Avidyne IFD4XX and IFD5XX FMS/GPS/Nav/Com Pilot Guides
P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800 P/N 600-00317-000 for the IFD545 and IFD550 P/N 600-00318-000 for the IFD510 P/N 600-00319-000 for the IFD410
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IFD5XX/4XX Installation Manual
Revision History
Document Number
600-00299-000
Control Category
Revision
Description
ECO
00
Initial Release
ECO-14-207
01
Release 10.0.1.0
ECO-14-283
02
Release 10.0.2.0
ECO-14-356
03
Release 10.0.3.0
ECO-14-424
04
Release for TSO
ECO-15-154
05
Define MLB100 TSO part number
ECO-15-385
06
Support WiFi Bluetooth activation utility
ECO-15-425
07
Release 10.1.1.0
ECO-15-469
08
Release 10.1.2.0
ECO-16-054
09
Add EASA Verbiage and 10.1.3
ECO-16-054
10
Release 10.2
ECO-17-001
11
Minor error correction to D-44, D-45, Table 73 ECO-17-060
12
Minor error correction to D-44, D-45, Table 73 ECO-17-066
13
Release 10.2.1.0
ECO-18-013
14
Release 10.2.1.0 minor corrections
ECO-18-066
15
Add Proline 21 EFIS /APS 3000 AP
ECO-18-138
16
Update for GPS roll-over of the 10 bit number of weeks, Update Table 1 and 2
ECO-19-025
17
Release 10.2.3.1
ECO-19-050
CC2 Date 07/09/14 08/21/14 11/12/14 02/02/15 04/09/15 09/29/15 11/06/15 12/04/15 03/01/16 06/23/16 02/03/17 03/08/17 03/15/17 02/09/18 03/07/18 05/16/18
02/08/19
04/17/19
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All materials copyrighted, including images that represent the software. Copyright 2014-2019 Avidyne Corporation. All rights reserved.
The latest installation manuals are available to authorized dealers on the web at www.avidyne.com.
Avidyne® is a registered trademark of Avidyne Corporation.
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Table of Contents
1. General Information ............................................................. 13
1.1
Introduction ........................................................................................................13
1.2
Applicability ........................................................................................................13
1.3
Unit Modifications ...............................................................................................15
1.4
Technical Specifications .....................................................................................16
1.4.1 IFD5XX Specifications ....................................................................................16
1.4.2 IFD4XX Specifications ....................................................................................20
1.5
Power Requirements..........................................................................................23
1.6
Regulatory Compliance ......................................................................................23
1.6.1 Applicable TSOs.............................................................................................23
1.6.2 TSO Deviations ..............................................................................................25
1.6.3 Non-TSO Functions........................................................................................26
1.6.4 Partial TSO Functions.....................................................................................27
1.6.5 Open Problem Report.....................................................................................27
1.7
Software and Hardware Design Assurance Levels..............................................27
1.8
Environmental Qualification Forms .....................................................................28
1.9
Databases .......................................................................................................... 29
1.10 Fault Detection and Exclusion (FDE) ..................................................................29
1.11 Part 23 STC Approved Model List.......................................................................30
1.12 Avidyne Supplied Material ..................................................................................31
1.12.1 Product Ship Kits ........................................................................................31
1.12.2 Optional Ship Kits .......................................................................................32
1.13 Materials Required but not Supplied ...................................................................33
2. Installation Considerations ................................................. 34
2.1
Plug & Play Considerations ................................................................................34
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2.2
Optional Installation Features .............................................................................35
2.3
IFD5XX/4XX Interfaces ......................................................................................36
2.4
Minimum System Configuration ..........................................................................42
2.4.1 VFR Installation ..............................................................................................42
2.4.2 IFR Installation ...............................................................................................43
2.5
Pre-Installation Checklist ....................................................................................45
3. Antenna Installation ............................................................. 46
3.1
Antenna Bonding................................................................................................46
3.2
Antenna Environmental Qualifications ................................................................46
3.3
GPS Antenna .....................................................................................................46
3.3.1 GPS Location .................................................................................................47
3.3.2 GPS Antenna Bonding....................................................................................49
3.3.3 GPS Antenna Cable .......................................................................................49
3.3.4 GPS Coaxial Cable Connector........................................................................50
3.3.5 Approved GPS Antennas................................................................................50
3.3.6 GPS Interference............................................................................................50
3.3.7 Ground Plane .................................................................................................51
3.3.8 Dual IFD5XX/4XX Installations .......................................................................51
3.3.9 Anti-Ice Protection ..........................................................................................51
3.4
VHF Communication Antenna ............................................................................51
3.4.1 Antenna Environmental Qualifications.............................................................51
3.4.2 VHF Communication Cable ............................................................................51
3.4.3 VHF Coaxial Cable Connector ........................................................................51
3.4.4 Voltage Standing Wave Ratio .........................................................................51
3.4.5 VHF Antenna..................................................................................................52
3.4.6 Antenna Ground Plane ...................................................................................52
3.5
Navigation Antennas ..........................................................................................52
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3.5.1 VOR/LOC Antenna .........................................................................................52
3.5.2 Navigation Coaxial Cable................................................................................52
3.5.3 Navigation Coaxial Cable Connector...............................................................52
3.5.4 Diplexer..........................................................................................................52
3.6
Glideslope Antenna ............................................................................................52
3.6.1 Glideslope ......................................................................................................52
4. Electrical Installation ........................................................... 53
4.1
Wire Type...........................................................................................................53
4.2
Wire and Connector Identification .......................................................................53
4.3
Wire Routing ......................................................................................................53
4.4
Shield Grounds ..................................................................................................53
4.5
Wire Harness Overbraid .....................................................................................53
4.5.1 Existing Equipment.........................................................................................53
4.5.2 Severe Lightning Transient Environment.........................................................53
4.5.3 Copper Overbraid Installation .........................................................................54
4.6
IFD5XX/4XX Connectors....................................................................................54
4.7
Byteflight Digital Data Bus Consideration Dual IFD Installations .......................54
4.7.1 Databus Wiring - Replacement Installations ....................................................54
4.7.2 Databus Wiring New Installations.................................................................55
4.8
Circuit Protection................................................................................................55
4.9
Power Distribution ..............................................................................................55
4.10 Electrical Load Analysis......................................................................................56
4.11 Low Power Behaviors.........................................................................................57
5. Mechanical Installation ........................................................ 58
5.1
Equipment Location New Installations..............................................................58
5.1.1 Determining the Field of View .........................................................................58
5.1.2 Navigation Annunciation .................................................................................59
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5.1.3 Course Deviation Indicator..............................................................................61
5.1.4 Instrument Panel Cutout .................................................................................61
5.1.5 Requirements for Tray Installation ..................................................................61
5.2
Equipment Location - Replacement Unit .............................................................62
5.3
Angle of Regard .................................................................................................62
5.4
Unit Installation/Removal ....................................................................................62
5.5
Internal Cooling ..................................................................................................62
5.6
External Cooling .................................................................................................62
5.7
Electrical Bonding...............................................................................................63
5.8
Aircraft Considerations .......................................................................................63
5.9
Weight and Balance ...........................................................................................63
5.10 Compass Safe Distance .....................................................................................63
6. System Installation............................................................... 64
6.1
Pin Function List.................................................................................................64
6.1.1 P1001 Main Connector ...................................................................................64
6.1.2 P1002 Communication Connector ..................................................................66
6.1.3 P1006 Navigation Connector ..........................................................................67
6.1.4 P1050 Additional I/O Connector......................................................................68
6.1.5 Altitude Gray Code .........................................................................................69
6.1.6 Heading Input .................................................................................................70
6.1.7 Main Course Deviation Indicator Output..........................................................70
6.1.8 Serial Data ..................................................................................................... 73
6.1.9 ARINC 429 .....................................................................................................73
6.1.10 ARINC 453 .................................................................................................74
6.1.11 RS170 Video ..............................................................................................74
6.1.12 Com/VOR/ILS Audio Electrical Characteristics............................................74
6.1.13 VOR/ILS Indicator Electrical Characteristics................................................76
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6.1.14 DME Tuning ...............................................................................................76
6.2
Bezel Lighting.....................................................................................................77
6.3
Traffic System ....................................................................................................78
6.4
Lightning Detection System ................................................................................78
6.5
Datalink Weather................................................................................................79
6.6
Audio Panels ......................................................................................................79
6.7
GAD 42 ..............................................................................................................80
6.8
Air Data System Sources....................................................................................80
6.9
Heading System Sources ...................................................................................81
6.10 Multifunction Displays.........................................................................................82
6.11 Forward Looking Terrain Alerting........................................................................83
6.11.1 Audio..........................................................................................................83
6.11.2 Annunciators ..............................................................................................83
6.12 TAWS/EGPWS Output .......................................................................................83
6.13 ADS-B Transponder/UAT Output........................................................................84
6.14 Autopilot .............................................................................................................87
6.15 Video Input .........................................................................................................87
6.16 Radar Display and Control..................................................................................88
7. Configuration and Checkout ............................................... 89
7.1
Wiring Check......................................................................................................89
7.2
Mounting Check .................................................................................................89
7.3
Chassis ID Setting..............................................................................................89
7.4
Unit Installation...................................................................................................90
7.5
Configuration ...................................................................................................... 90
7.5.1 Maintenance Mode .........................................................................................90
7.5.2 ARINC 429 Port Configuration (Page 1)..........................................................91
7.5.3 RS-232 Port Configuration (Page 2)................................................................96
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7.5.4 Main System Configuration (Page 3).............................................................100
7.5.5 Main Input Configuration (Page 4) ................................................................103
7.5.6 Main Lighting Configuration (Page 5) ............................................................104
7.5.7 Main Discrete I/O (Page 6) ...........................................................................108
7.5.8 Main CDI/OBS Config Page (Page 7) ...........................................................109
7.5.9 VOR/LOC/GS CDI (Page 8)..........................................................................112
7.5.10 VOR/LOC/GS ARINC 429 Configuration (Page 9).....................................114
7.5.11 GPS Vertical Offset (Page 10) ..................................................................115
7.5.12 GDL Configuration Pages (Page 11).........................................................116
Remote XPDR Configuration (Page 12)............................................................117
7.5.14 Network (WiFi) Setup (Page 13)................................................................118
7.5.15 Bluetooth Setup (Page 14)........................................................................126
7.5.16 IRU Calibration, IFD545, IFD550 (Page 15) ..............................................127
7.5.17 RDR2000 Radar Configuration (Page 16) .................................................129
7.5.18 Stormscope Test Page (Page 17) .............................................................131
7.5.19 GAD 42 Configuration...............................................................................131
7.5.20 Other System Diagnostics Pages..............................................................132
7.6
Checkout .......................................................................................................... 134
7.6.1 Database Check...........................................................................................134
7.6.2 Airplane Flight Supplement Check ................................................................134
7.6.3 Instructions for Continued Airworthiness .......................................................134
7.6.4 Aircraft Weight and Balance..........................................................................134
7.6.5 Electrical Load Analysis................................................................................135
7.6.6 GPS Signal Acquisition.................................................................................135
7.6.7 VHF COM Checkout.....................................................................................135
7.6.8 VOR/LOC/ GS Checkout ..............................................................................136
7.6.9 Autopilot .......................................................................................................136
7.6.10 Magnetic Compass Swing.........................................................................136
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7.6.11 IFD5XX/4XX Bezel and Display Lighting ...................................................136 7.6.12 External Annunciators and Switches .........................................................136
7.6.13 Placards ...................................................................................................136
7.6.14 Self-test Page...........................................................................................137 7.6.15 Dual IFD5XX/4XX Configuration ...............................................................138
7.6.16 Heading Interface Check ..........................................................................138 7.6.17 ADS-B Output...........................................................................................138
8. Flight Checks ...................................................................... 139
8.1
GPS Verification...............................................................................................139
8.2
VHF COM Flight Check ....................................................................................139
8.3
VOR Flight Checks...........................................................................................139
8.4
ILS Flight Checks .............................................................................................139
8.5
Autopilot Checks ..............................................................................................139
8.6
Sensors Verification..........................................................................................140
9. Glove Validation Procedures ............................................ 141
10. Software and Database Update Procedures ............. 142
10.1 Data Updates ...................................................................................................142
10.2 Datalogs Download ..........................................................................................145 10.3 Software Update...............................................................................................147
11. Periodic Maintenance .................................................. 148
11.1 Equipment Calibration ......................................................................................148 11.2 VOR Checks ....................................................................................................148
11.3 Cleaning...........................................................................................................148
12. Factory Service Policies and Procedures ................. 149
12.1 Technical Support ............................................................................................149
12.2 General Service Procedures.............................................................................149
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13. Bezel and Display Cleaning......................................... 150 Appendix A: Environmental Qualification Form ................... 151 Appendix B: STC Permission .................................................. 153 Appendix C: Mechanical Drawings ......................................... 154 Appendix D: Electrical Interface Drawings ............................ 162 Appendix E: Troubleshooting Guide ...................................... 240 Appendix F: Configuration Setup ........................................... 242
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Notes to Installers:
The following important issues regarding the Avidyne 700-00182-XXX and 700-00179-XXX GPS/NAV/COM System installation should be noted during the planning stages.
1. These installation instructions assume that the GPS/NAV/COM transceiver and GPS antenna can be installed in a structurally sound manner in accordance with the installation manual and AC 43.13-( ). All the aircraft certification requirements must remain in compliance.
2. Mounting the GPS antenna on composite and pressurized aircraft requires engineering guidance beyond the scope of this manual. With respect to the Approved Model List STC, the physical mounting of the antenna is specifically excluded from the approval in the case of installations on the pressure vessel of pressurized aircraft, composite aircraft, and aircraft with a certification basis of Amendment 23-45 or later, unless approved installation data is listed in the Master Document List of the STC. All early amendment, metal construction, non-pressurized aircraft antenna installations must be installed consistent with accepted industry practices. The installation must be structurally sound and in accordance with FAA Advisory Circular 43.13-1B and 43.13-2B. All other antennas must be mounted using the manufacturers' installation data.
3. An Electrical Load Analysis must be accomplished to determine that the electrical limits of the specific aircraft are not exceeded. The Electrical Load Analysis, Functional Hazard Assessment and other certification requirements for the aircraft must remain in compliance.
4. The IFD5XX/4XX Forward Looking Terrain Alerting is not a TSO-C151 system, and does not satisfy any Part 91/135 TAWS requirements.
5. Prior to starting IFD5XX/4XX installation, verify the aircraft make and model is on the STC Approved Model List (AML). Also, note any installation specific data for the make and model in the AML.
6. IFD545 and IFD550 may not be stored, or installed in any aircraft that is expected to be stored, in areas where the temperature is expected to be below -40°C
7. IFD545 and IFD550 cannot be used as a required attitude indicator and must only be used as a "secondary (non required) source of attitude information".
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1. General Information
1.1 Introduction
This manual contains information about the physical, mechanical, and electrical characteristics of the Avidyne IFD5XX/IFD4XX GPS/Navigation/Communication, and provides installation instructions for its components.
1.2 Applicability
This manual applies to the following part numbers in Table 1 and Table 2
1 This component is only present in 530-00243-000 configurations and specified 700-00182-XXX Configurations
2 This component is only present in 530-00243-001 configurations specified 700-00182-XXX Configurations
Model Number
Hardware Part
Software Part Number
Number
(or later approved revision)
IFD510 (Black Bezel) IFD510 with Video (Black Bezel)
IFD510 (Gray Bezel) IFD510 with Video (Gray Bezel)
IFD510 (Black Bezel) IFD510 with Video (Black Bezel)
IFD510 (Gray Bezel) IFD510 with Video (Gray Bezel)
IFD540 (Black Bezel) IFD540, 16W (Black Bezel) IFD540 with Video (Black Bezel)
IFD540 (Gray Bezel) IFD540, 16W (Gray Bezel) IFD540 with Video (Gray Bezel)
IFD540 (Black Bezel) IFD540 with Video (Black Bezel)
IFD540 (Gray Bezel) IFD540 with Video (Gray Bezel)
IFD545 (Black Bezel) IFD545 with Video (Black Bezel)
IFD545 (Gray Bezel) IFD545 with Video (Gray Bezel)
IFD545 (Black Bezel) IFD545 with Video (Black Bezel)
IFD545 (Gray Bezel) IFD545 with Video (Gray Bezel)
700-00182-010(1) 700-00182-011(1) 700-00182-110(1) 700-00182-111(1) 700-00182-710(2) 700-00182-711(2) 700-00182-810(2) 700-00182-811(2) 700-00182-000(1) 700-00182-002(1) 700-00182-001(1) 700-00182-100(1) 700-00182-102(1) 700-00182-101(1) 700-00182-700(2) 700-00182-701(2) 700-00182-800(2) 700-00182-801(2) 700-00182-030(1) 700-00182-031(1) 700-00182-130(1) 700-00182-131(1) 700-00182-730(2) 700-00182-731(2) 700-00182-830(2) 700-00182-831(2)
ACR: 530-00240-000 Rev. 03(1) 530-00240-001 Rev. 00(2) · 510-00340-000 Rev. 00 · 510-00341-000 Rev. 00 · 510-00310-000 Rev. 00 · 510-00311-001 Rev. 00 · 510-00312-000 Rev. 04(1) · 510-00312-005 Rev 00 (2) · 510-00346-000 Rev. 00
FPSM: 530-00226-000 Rev. 04 · 510-00294-000 Rev. 04 · 510-00291-000 Rev. 00
LIO App: 530-00239-000 Rev. 05 · 510-00328-000 Rev. 00 · 510-00329-000 Rev. 05
LIO I/O: 530-00238-000 Rev. 05 · 510-00343-000 Rev. 00 · 510-00289-000 Rev. 01 · 510-00290-000 Rev. 02 · 510-00291-000 Rev. 00
GPS: 530-00229-000 Rev. 08 · 510-00876-000 Rev. 07 · 510-00877-000 Rev. 02
VHF: 530-00231-000 Rev. 04 NOTE: Not Installed in IFD510, IFD545
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IFD550 (Black Bezel) IFD550 with Video (Black Bezel)
IFD550 (Gray Bezel) IFD550 with Video (Gray Bezel)
IFD550 (Black Bezel) IFD550 with Video (Black Bezel)
IFD550 (Gray Bezel) IFD550 with Video (Gray Bezel)
IFD5XX/4XX Installation Manual
700-00182-020(1) 700-00182-021(1) 700-00182-120(1) 700-00182-121(1) 700-00182-720(2) 700-00182-721(2) 700-00182-820(2) 700-00182-821(2)
· 510-00314-000 Rev. 00 · 510-00239-001 Rev. 00 · 510-00316-000 Rev. 05 · 510-00237-000 Rev. 00 ARS: 530-00223-000 Rev. 00 NOTE: Installed in IFD545 and IFD550 · 510-00283-000 Rev. 01 · 510-00332-000 Rev. 00
Table 1 IFD5XX Variants
1 This component is only present in 530-00243-000 configurations and specified 700-00179-XXX Configurations 2 This component is only present in 530-00243-001 configurations specified 700-00179-XXX Configurations
Model Number
Hardware Part Number
Software Part Number (or later approved revision)
IFD410 (Black Bezel) IFD410 (Gray Bezel) IFD410 (Black Bezel) IFD410 (Gray Bezel)
IFD440 (Black Bezel IFD440 (Gray Bezel) IFD440 (Black Bezel IFD440 (Gray Bezel)
700-00179-010(1) 700-00179-110(1) 700-00179-710(2) 700-00179-810(2)
700-00179-000(1) 700-00179-100(1) 700-00179-700(2) 700-00179-800(2)
ACR: 530-00240-000 Rev. 03(1) 530-00240-001 Rev. 00(2) · 510-00340-000 Rev. 00 · 510-00341-000 Rev. 00 · 510-00310-000 Rev. 00 · 510-00311-001 Rev. 00 · 510-00312-000 Rev. 04(1) · 510-00312-005 Rev 00 (2) · 510-00346-000 Rev. 00
FPSM: 530-00226-000 Rev. 04 · 510-00294-000 Rev. 04 · 510-00291-000 Rev. 00
LIO App: 530-00239-000 Rev. 05 · 510-00328-000 Rev. 00 · 510-00329-000 Rev. 05
LIO I/O: 530-00238-000 Rev. 05 · 510-00343-000 Rev. 00 · 510-00289-000 Rev. 01 · 510-00290-000 Rev. 02 · 510-00291-000 Rev. 00
GPS: 530-00229-000 Rev. 08 · 510-00876-000 Rev. 07 · 510-00877-000 Rev. 02
VHF: 530-00231-000 Rev. 04 NOTE: Not Installed in IFD410
· 510-00314-000 Rev. 00 · 510-00239-001 Rev. 00 · 510-00316-000 Rev. 05 · 510-00237-000 Rev. 00
Table 2 IFD4XX Variants
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1.3 Unit Modifications
The following tables list the hardware modifications since initial release of the IFD540 and IFD440. The IFD510, IFD545, IFD550 and IFD410 do not have any unit modifications at the time of this revision.
Modification
Change
Hardware PN
Hardware Revision
Software
HW Release Date
MOD 2 MOD 4 MOD 5 MOD 8 MOD 11 MOD 12
OBS UPDATE
700-00182-000
01
700-00182-002
01
700-00182-100
01
700-00182-102
01
700-00182-000
03
SERIAL DME UPDATE
700-00182-002 700-00182-100
03 03
700-00182-102
03
700-00182-000
04
STANDBY AUDIO
700-00182-002
04
IMPLEMENTATION
700-00182-100
04
700-00182-102
04
700-00182-000
07
GPS MAXIM B, HIGH 700-00182-002
07
GAIN LNA1
700-00182-100
07
700-00182-102
07
REPLACEMENT OF MAIN GPS
OSCILLATOR
700-00182-000 700-00182-002 700-00182-100 700-00182-102
10 10 10 10
CHANGE RESOLVER INPUTS TO AC COUPLED
700-00182-000 700-00182-002 700-00182-100 700-00182-102
11 11 11 11
Table 3 IFD540 Modification History
10.0.0.0 or later
9/25/2014
10.0.3.0 or later
11/21/2014
10.1 or later 12/11/2014 10.1 or later 05/05/2015 10.1 or later 07/22/2015 10.1 or later 11/04/2015
Modification
Change
Hardware PN
Hardware Revision
Software
HW Release Date
MOD 03
CHANGE RESOLVER INPUTS TO AC COUPLED
700-00179-000 700-00179-100
03 03
Table 4 IFD440 Modification History
10.1 or later 11/04/2015
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1.4 Technical Specifications
This section gives mechanical and electrical characteristics for the IFD5XX and IFD4XX.
1.4.1 IFD5XX Specifications
The IFD5XX unit has the following characteristics: 1.4.1.1 IFD5XX Physical and Electrical Specifications
Physical Specifications
Bezel Height
4.58 inches (116 mm)
Bezel Width
6.25 inches (159 mm)
Depth (w/Connectors)
11.00 inches (279 mm)
Weight
Table 10 IFD Installed weights
Connectors (Aircraft Mating Connector)
P1001/P1050 - 78-position High Density DSubminiature (male)
P1002- 25-position Standard D- Subminiature (female)
P1006- 44-position High Density DSubminiature (male)
Electrical Requirements
Voltage Current
Dimming Bus
9-33 VDC
IFD510: 4.4A main at 14VDC 3.0A main at 28VDC IFD540: 4.4A main, 6.5A COM, 0.5A NAV at 14VDC 3.0A main, 1.0A NAV at 28VDC 3.6A @ 10W, 4.1A @ 16W COM at 28VDC IFD550: 5.4A main, 6.5A COM, 0.5A NAV at 14VDC 3.5A main, 1.0A NAV at 28VDC 3.6A @ 10W, 4.1A @ 16W COM at 28VDC IFD545: 5.4A main at 14VDC 3.5A main at 28VDC
28VDC/14VDC/5VDC/5VAC
Cooling Requirements
Not Required
Operating Limits
Reference Appendix A: Environmental Qualification Form
Table 5 IFD5XX Specifications
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1.4.1.2 IFD5XX Display Specifications
Display Size Active Area Resolution Viewing Angle
5.7 inches diagonal
4.53 inches (w) x 3.40 inches (h)
640x480 pixels
IFD5XX Designed and Tested Limits:
Left/Right: 45°
Up:
35°
Down: 35°
LCD Specification:
Left/Right: 80°
Up:
80°
Down: 60°
Table 6 IFD5XX Display Specifications
1.4.1.3 IFD5XX GPS Specifications
Channels Velocity TTFF (Time to First Fix) Reacquisition Position Update Interval PPS Signal (Time Mark)
Lat/Long Position Accuracy Fault Detection/RAIM Sensitivity GPS System Design Assurance (SDA) GPS Source Integrity Level (SIL) Source Integrity Level Supplement (SILSUPP) Navigation Accuracy Category Velocity (NACV)
Receiver Class
16 channels (13 GPS, 3 GPS/WAAS/SBAS)
1000 knots maximum (below 60,000 ft)
150 seconds
20 seconds
0.2 seconds (5 Hz)
(UTC Epoch) +100ns ± 50ns over all conditions 1 sec ±75ns between pulses 3.4 meters
RAIM/FDE WAAS Beta 3 Compliant @ 5 Hz
-123 dBm
DO-178B Level B, DO-254 Level B
3 Enroute
0 "per hour"
Category 3 [< 1 m/s] ADS-B installations should use a NACv of 1 unless GPS tests support a higher category. The AXP340 requires a NACv of Category 1 [< 10 m/s] or better.
TSO-C146d Class Gamma 3 receiver that complies with AC 20-138C
Table 7 IFD5XX GPS Specifications
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1.4.1.4 IFD540, IFD550 VHF Communication Transceiver Specification
Audio Output Audio Response AGC Characteristics Sensitivity
Spurious Response
Transmitter Power Transmitter Duty Cycle Modulation Capability Carrier Noise Level Frequency Stability Demodulation Audio Distortion Sidetone Fidelity Demodulation Audio Response
65 mW into 150 load <6dB Variation from 350 to 2500 Hz, 4kHz -18dB <6dB Variation from 10uV to 10mV 4uV (6dB (S+N)/N 30% mod @ 1KHz) 10mV spurious signal produces no more output than a desired signal at 6dB (S+N)/N 16W or 10W @ 28V, 10W @ 14V (Typical) Recommended 10% maximum 70% -39dB (S+N)/N >2.5 ppm
<12% @ 70% modulation
300-2500 Hz
<6dB Variation from 300 to 2500 Hz
Table 8 VHF Communication Transceiver Specifications
1.4.1.5 IFD545, IFD550 ARS (Inertial Reference) Specifications
Attitude Static Accuracy Attitude Dynamic and Flight Accuracy Slip output Heading, Turn Rate, and Standard Turn Bank Angle Outputs
+/- 1.0 degree +/- 2.5 degrees Provided Not provided
Table 9 ARS Specification
1.4.1.6 IFD5XX Installed unit weight in pounds
Unit
IFD510 IFD540 IFD545 IFD550
Unit Weight
5.65 6.75 6.00 7.15
Installed Weight Without Backshells (Less Wiring)
7.04 8.38 7.39 8.78
Table 10 IFD Installed weights
Installed Weight with Backshells (Less Wiring)
7.52 9.20 7.87 9.60
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1.4.1.7 IFD540, IFD550 VHF Navigation Specification
Glideslope Receiver
Selectivity
Sensitivity (flag) Spurious Response Centering Accuracy Deflection Response Localizer Receiver Selectivity Sensitivity (flag) Sensitivity (aural) Centering Accuracy Deflection Response
Audio Response
0 +/-.0091 ddm w/ test signal varied +/-17kHz. 60dB for +/- 132kHz offset 10uV max >-60 dB 0 ± 0.02 DDM or better 67% of final value in 600msec 6dB at least ±17kHz, 40dB no more than ±80kHz 10uV max 10uV max for 20dB (S+N)/N with 1kHz 30%mod +/-3mV 67% of final value in 600msec <6dB Variation from 350 to 2500 Hz, -20dB <150Hz >9kHz
Table 11 VHF Navigation Specification
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1.4.2 IFD4XX Specifications
The IFD4XX unit has the following characteristics: 1.4.2.1 IFD4XX Physical and Electrical Specifications
Physical Specifications
Bezel Height
2.66 inches (67 mm)
Bezel Width
6.25 inches (159 mm)
Depth (w/Connectors)
11.00 inches (279 mm)
Weight
Table 13 IFD Installed weights
Connectors (Aircraft Mating Connector)
P1001 - 78-position High Density DSubminiature (male)
P1002- 25-position Standard D- Subminiature (female)
P1006- 44-position High Density DSubminiature (male)
Electrical Requirements
Voltage
9-33 VDC
Current
IFD410:
4.4A main at 14VDC
3.0A main at 28VDC
IFD440:
4.4A main, 6.5A COM, 0.5A NAV at 14VDC
3.0A main, 1.0A NAV at 28VDC
3.6A @ 10W, 4.1A @ 16W COM at 28VDC
Dimming Bus
28VDC/14VDC/5VDC/5VAC
Cooling Requirements
Not Required
Operating Limits
Reference Appendix A: Environmental Qualification Form
Table 12 IFD4XX Specifications
1.4.2.2 IFD4XX Installed unit weight in pounds
Unit
IFD410 IFD440
Unit Weight
4.00 5.16
Installed Weight Without Backshells (Less Wiring)
4.81 6.21
Table 13 IFD Installed weights
Installed Weight with Backshells (Less Wiring)
5.05 6.78
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1.4.2.3 IFD4XX Display Specifications
Display Size Active Area Resolution Viewing Angle
4.8 inches diagonal
4.53 inches (w) x 1.70 inches (h)
640x480 pixels
IFD4XX Designed and Tested Limits:
Left/Right: 45°
Up:
35°
Down: 35°
LCD Specification:
Left/Right: 80°
Up:
80°
Down: 60°
Table 14 IFD4XX Display Specifications
1.4.2.4 IFD4XX GPS Specifications
Channels Velocity TTFF (Time to First Fix) Reacquisition Position Update Interval PPS Signal (Time Mark)
Lat/Long Position Accuracy Fault Detection/RAIM Sensitivity GPS System Design Assurance (SDA) GPS Source Integrity Level (SIL) Source Integrity Level Supplement (SILSUPP) Navigation Accuracy Category Velocity (NACV)
Receiver Class
16 channels (13 GPS, 3 GPS/WAAS/SBAS) 1000 knots maximum (below 60,000 ft) 150 seconds 20 seconds 0.2 seconds (5 Hz) (UTC Epoch) +100ns ± 50ns over all conditions 1 sec ±75ns between pulses 3.4 meters RAIM/FDE WAAS Beta 3 Compliant @ 5 Hz -123 dBm DO-178B Level B, DO-254 Level B
3 Enroute 0 "per hour"
Category 3 [< 1 m/s] ADS-B installations should use a NACv of 1 unless GPS tests support a higher category. The AXP340 requires a NACv of Category 1 [< 10 m/s] or better. TSO-C146d Class Gamma 3 receiver that complies with AC 20-138C
Table 15 IFD4XX GPS Specifications
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1.4.2.5 IFD440 VHF Communication Transceiver Specifications
Audio Output Audio Response AGC Characteristics Sensitivity
Spurious Response
Transmitter Power Transmitter Duty Cycle Modulation Capability Carrier Noise Level Frequency Stability Demodulation Audio Distortion Sidetone Fidelity Demodulation Audio Response
65 mW into 150 load <6dB Variation from 350 to 2500 Hz, 4kHz -18dB <6dB Variation from 10uV to 10mV 4uV (6dB (S+N)/N 30% mod @ 1KHz) 10mV spurious signal produces no more output than a desired signal at 6dB (S+N)/N 16W or 10W @ 28V, 10W @ 14V (Typical) Recommended 10% maximum 70% -39dB (S+N)/N >2.5 ppm
<12% @ 70% modulation
300-2500 Hz
<6dB Variation from 300 to 2500 Hz
Table 16 VHF Communication Transceiver Specifications
1.4.2.6 IFD440 VHF Navigation Specification
Glideslope Receiver
Selectivity
Sensitivity (flag) Spurious Response Centering Accuracy Deflection Response Localizer Receiver Selectivity Sensitivity (flag) Sensitivity (aural) Centering Accuracy Deflection Response
Audio Response
0 +/-.0091 ddm w/ test signal varied +/-17kHz. 60dB for +/- 132kHz offset 10uV max >-60 dB 0 ± 0.02 DDM or better 67% of final value in 600msec 6dB at least ±17kHz, 40dB no more than ±80kHz 10uV max 10uV max for 20dB (S+N)/N with 1kHz 30%mod +/-3mV 67% of final value in 600msec <6dB Variation from 350 to 2500 Hz, -20dB <150Hz >9kHz
Table 17 VHF Navigation Specification
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1.5 Power Requirements
The IFD5XX/4XX is capable of operating from 9-33 VDC. The following table shows the maximum current requirements for 14VDC and 28VDC aircraft electrical systems.
Voltage
14VDC
Main Power IFD540/510/440/410
4.4A
Main Power IFD550/545
5.4A
COM Power 10W*
6.5A
COM Power 16W*
N/A
NAV Power*
0.5A
*Not applicable for IFD510/ 545/410
Table 18 Power Requirements
28VDC
3.0A 3.5A 3.6A 4.1A 1.0A
1.6 Regulatory Compliance
1.6.1 Applicable TSOs
This section identifies Technical Standard Orders (TSOs) applicable to the IFD5XX/4XX system. The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approvals for installation in aircraft. The article may be installed only if performed under 14 CFR Part 43 or the applicable airworthiness requirements.
TSO Number
Title
Type/Categories
TSO-C34e*
ILS Glide Slope Receiving Equipment Operating within the Radio Frequency Range of 328.6-335.4 Megahertz (MHz)
TSO-C36e*
Airborne ILS Localizer Receiving Equipment Operating within the Radio Frequency Range of 108-112 Megahertz
(MHz)
TSO-C40c*
VOR Receiving Equipment Operating within the Radio Frequency Range of
108-117.95 Megahertz (MHz)
TSO-C44c TSO-C63d
Fuel Flowmeters Airborne Weather Radar Equipment
Class C (Display Functions Only)
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TSO Number
Title
Type/Categories
TSO-C110a
Airborne Passive Thunderstorm Detection Equipment
TSO-C112e
Air Traffic Control Radar Beacon System/Mode Select (ATCRBS/Mode S)
Airborne Equipment
TSO-C113a
Airborne Multipurpose Electronic Display
TSO-C118a
Traffic Alert and Collision Avoidance System (TCAS) Airborne Equipment,
TCAS I
TSO-C128a*
Devices that Prevent Blocked Channels Used in Two-Way Radio
Communications Due to Unintentional Transmissions
TSO-C146d
Stand-Alone Airborne Navigation Equipment Using the Global Positioning System (GPS) Augmented by the Wide
Area Augmentation System (WAAS).Airborne Supplemental Navigation Equipment Using the Global Positioning System (GPS) - Gamma 3
TSO-C147a
Traffic Advisory System (TAS) Airborne Class A (Display Functions
Equipment
Only)
TSO-C157a
Aircraft Flight Information Services Broadcast (FIS-B) Datalink Systems and
Equipment
TSO-C165
Electronic Map Display Equipment for Graphical Depiction of Aircraft Position
TSO-C169a*
VHF Radio Communications Transceiver Equipment Operating Within The Radio
Frequency Range 117.975 To 137.000 Megahertz
Class C, E, 3 and 5
TSO-C195b
Avionics Supporting Automatic Dependent Surveillance Broadcast ADS-B Aircraft Surveillance Applications
TSO-C201
Attitude and Heading Reference Systems AHRS
A4HXT7
*Not applicable for IFD510/ 545/410
Table 19 IFD5XX/4XX TSO Functions
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1.6.2 TSO Deviations
TSO TSO-C34e - ILS Glideslope Receiving
Equipment TSO-C36e - Airborne ILS Localizer Receiving
Equipment TSO-C40c - VOR Receiving Equipment
TSO-C44c - Fuel Flowmeters
TSO-C110a Airborne Passive Thunderstorm Detection Equipment
TSO-C113a Airborne Multipurpose Electronic Display
TSO-C118a - Traffic Alert and Collision Avoidance System (TCAS) Airborne Equipment, TCAS I
TSO-C128a - Equipment that Prevents Blocked Channels used in two-ways Radio Communications due to unintentional transmissions
IFD5XX/4XX Installation Manual
Deviation(s)
1. Environmental qualification performed in accordance with DO160G rather than DO-160B.
1. Environmental qualification performed in accordance with DO160G rather than DO-160B.
1. Environmental qualification performed in accordance with DO160G rather than DO-160B.
1. Environmental qualification performed in accordance with DO160G rather than a combination of DO-160B and AS407C. AS407C requirements apply to portions of the instrument not implemented by the IFD system;
2. The fuel flow indicators will not use matte white material for all graduations, numerals, pointers and indicators. Color coded indications are used where appropriate for rapid pilot recognition of exceedances;
3. The fuel flow indicators are a digital readout instead of pointer and dial.
1. Environmental qualification performed in accordance with DO160G rather than DO-160B.
1. The IFD5XX/4XX display response time is not less than 1 second during Short-Time Operating Low Temperature environmental conditions as defined in Section 4.0 of RTCA/DO-160G.
1. The IFD5XX/4XX used the exceptions listed in appendix 1 of TSO-C147 in lieu of the corresponding minimum operational performance standards specified in the TSO.
1. Environmental qualification performed in accordance with DO160G rather than DO-160B.
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TSO
Deviation(s)
TSO-C146d - Stand-alone Airborne Navigation Equipment using the Global Position System augmented by the Satellite based Augmentation System
1. Environmental qualification performed in accordance with DO160G rather than DO-160B.
TSO-C147a Traffic Advisory System (TAS) Airborne Equipment
1. The IFD5XX/4XX map does not place a range ring at 2 NM from the own aircraft symbol when a display range of 10 NM or less is selected;
TSO-C157a Aircraft Flight Information Services Broadcast (FIS-B) Data Link Systems and Equipment
1. Smoothing and scaling algorithms at high map ranges remove small patches of high-intensity NEXRAD returns in favor of surrounding lower-intensity returns.
TSO-C165 Electronic Map Display Equipment for Graphical Depiction of Aircraft Position
1. De-cluttering on chart page not provided.
2. Location of traffic symbols in the absence of heading information
TSO-C169a - VHF Radio Communications Transceiver Equipment
1. Environmental qualification performed in accordance with DO160G rather than DO-160B.
TSO-C201 - Attitude and Heading Reference Systems AHRS
1. The IFD5XX/4XX system does not provide minor graduations at 5° intervals on the heading indicator
Table 20 IFD5XX/4XX TSO Deviations
Table 20 above lists the TSO Deviations and a brief description of the nature of the deviation that have been granted for those applicable TSOs.
1.6.3 Non-TSO Functions
The following IFD5XX/4XX functions are not TSO'd:
IFD5XX/4XX Function
Display of Terrain Alerting Display of Aircraft Checklists Calculators (Air Data, Fuel Planner, etc)
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IFD5XX/4XX Function
Display of Timers and Schedulers Display of RS-170 Video from an approved device
Synthetic Vision Display of Navigation Charts
WiFi in and out Bluetooth in
Auxiliary Radar Display (IFD4XX only)
Table 21 Non-TSO Functions
1.6.4 Partial TSO Functions
The following IFD5XX/4XX TSOs are partial function:
TSO
Description
Comment
TSO-C44c
Fuel Flowmeters
Display Only
TSO-C110a
Airborne Passive Thunderstorm Detection Equipment
Display Only
TSO-C118a
Traffic Alert and Collision Avoidance System (TCAS) Airborne Equipment,
TCAS I
Display Only
TSO-C147a
Traffic Advisory System (TAS) Airborne Equipment
Display Only
TSO-C157a
Aircraft Flight Information Services Broadcast (FIS-B) Datalink Systems and
Equipment
Display Only
Table 22 Partial Function TSOs
1.6.5 Open Problem Report
At the time of this revision, the IFD5XX/4XX does not have any open problems that affect safety or design assurance level of the unit.
1.7 Software and Hardware Design Assurance Levels
The IFD5XX/4XX contains software developed in accordance with DO-178B Level B, C, and D design assurance levels. The following table lists functions of the IFD5XX/4XX system and their corresponding software design assurance level.
All complex electronic hardware devices were developed in compliance with DO-254 Level B.
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Component IFD5XX/4XX
Function
Traffic
Lightning Digital Moving Map (including Terrain and Synthetic
Vision Display) Terrain Alerting
Wx Datalink
FMS
VHF Communication (N/A for IFD510/545/410)
VHF Navigation (N/A for IFD510/545/410)
GPS Navigation
Checklist
Fuel Display Charts
(N/A for IFD510/545/410) Timers/Schedulers
Calculators
Maintenance Mode
DO-178B Design Assurance Level
C D
C
C D B (Precision Approach) C (All other Functions) C
C B C C C
C C D
Airborne Weather Radar
C
Display of External Video
C
Data to ADS-B Out
C
Table 23 DO-178B Software Design Assurance Levels
1.8 Environmental Qualification Forms
The environmental Qualification for the IFD5XX/4XX is listed in Appendix A: Environmental Qualification Form.
Note: If the IFD5XX/4XX has been exposed to extreme cold temperature prior to start, it may take a warm up period to achieve standard performance.
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1.9 Databases
The IFD5XX/4XX utilizes several databases. All the databases can be loaded on the IFD using the USB port on the IFD. Reference the IFD5XX or IFD4XX Pilot's Guide for updating the IFD5XX/4XX databases.
1.10 Fault Detection and Exclusion (FDE)
FDE software is part of all IFD5XX/4XX systems and does not require any installer or pilot action to operate. This FDE software is running at all times and if it detects an issue, it will alert the pilot through Caution-Alerting System (CAS) messages.
When the IFD5XX/4XX is installed per the directions in this Installation Manual, it complies with the governing requirements for GPS Primary Means of Navigation in Oceanic and Remote Airspace (more than 200 nm from the nearest airport), when used with any commercially available RAIM/FDE Prediction Program. Examples of these prediction programs include the FAA's raimprediction.net, Fltplan.com, www.sapt.faa.gov, and the Garmin FDE Prediction Program.
These programs only need to be run under the following scenarios for 14 CFR Parts 91, 121, 125, and 135 operations where the IFD5XX/4XX is being used as the primary means of navigation and:
· TSO-C146d compliant antenna equipped aircraft that experience a WAAS failure or when operating outside of SBAS coverage areas;
· Non-TSO-C146d compliant antenna equipped aircraft (e.g. TSOC129a only compliant systems) when operating in Oceanic and Remote airspace, Enroute and Terminal airspace, or during any LNAV/VNAV, LP, or LPV approach.
Prior to conducting Class II navigation (remote/oceanic), the owner/operator must obtain operational approval for using the IFD5XX/4XX system for long-range navigation from the appropriate flight standards district office.
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1.11 Part 23 STC Approved Model List
The aircraft listed on the Approved Model List STC are eligible to install the IFD5XX/4XX. However, the installer must determine if the installation is in compliance with the limitations stated in the STC and this manual. Any deviations from the STC and/or this manual must have a separate installation approval.
The aircraft listed on the Part 27 Helicopter Approved Model List STC are eligible to install the IFD5XX/4XX in the helicopters listed in the STC Approved Model List. However, the installer must determine if the installation is in compliance with the limitations stated in the STC and this manual. Any deviations from the STC and/or this manual must have a separate installation approval.
Installations in Part 25/27/29 aircraft or Part 23 airplanes not listed on the AML STC may install the IFD5XX/4XX, however, it will require additional installation approval (e.g. Field approval, STC, or TC amendment), reference FAA Advisory Circular 23-22 as needed. If installing a IFD5XX/4XX on a Part 27/29 aircraft via field approval, the Avidyne Helicopter tray must be used, reference Table 26 and Table 27. Reference the IFD5XX/4XX Helicopter Installation Manual 600-00333-000.
The installation of antennas on composite and/or pressurized aircraft requires engineering guidance beyond the scope of this manual. With respect to the Approved Model List STC, the physical mounting of the antenna is specifically excluded from the approval in the case of installation on the pressure vessel of a pressurized aircraft, composite aircraft, and aircraft with a certification basis of Amendment 23-45 or later, unless approved installation data is listed in the Master Document List of the STC. All early amendment, metal construction, nonpressurized aircraft may install the GPS antenna using this manual. The installation must be structurally sound and in accordance with FAA Advisory Circular 43.13-( ). All other antennas must be installed using the antenna manufacturer's installation data or FAA Advisory Circular 43.13-( ).
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1.12 Avidyne Supplied Material
The following Ship Kits are available for ordering from Avidyne Corporation. The Part 27 Helicopter ship kits are listed in the IFD5XX/4XX Helicopter Installation Manual 600-00333000.
Note: Ship Kit content and/or Part numbers may change without notice, verify before ordering.
1.12.1 Product Ship Kits
Component IFD540 Unit IFD510 Unit IFD545 Unit IFD550 Unit
Ship Kit Black Bezel
Ship Kit Gray Bezel
Ship Kit Black Bezel With Video
850-00182-000 850-00182-700
850-00182-100 850-00182-800
850-00182-001 850-00182-701
850-00182-010 850-00182-710
850-00182-110 850-00182-810
850-00182-011 850-00182-711
850-00182-030 850-00182-730
850-00182-130 850-00182-830
850-00182-031 850-00182-731
850-00182-020 850-00182-720
850-00182-120 850-00182-820
850-00182-021 850-00182-721
Table 24 IFD5XX Ship Kit
Ship Kit Gray Bezel With Video
850-00182-101 850-00182-801
850-00182-111 850-00182-811
850-00182-131 850-00182-831
850-00182-121 850-00182-821
Component
Ship Kit Black Bezel
Ship Kit Gray Bezel
IFD440 Unit IFD410 Unit
850-00179-000 850-00179-700
850-00179-100 850-00179-800
850-00179-010 850-00179-710
850-00179-110 850-00179-810
Table 25 IFD4XX Ship Kit
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1.12.2 Optional Ship Kits
Component
Fixed Wing Aircraft Ship Kits
IFD5XX Tray
850-00188-000
IFD5XX Install kit (no tray) IFD540 & IFD550
820-00113-000
IFD5XX Install kit (no tray) IFD510 & IFD545
820-00113-001
IFD5XX Tray and Install Kit IFD540 & IFD550
850-00188-002
IFD5XX Tray and Install Kit IFD510 & IFD545
850-00188-004
Table 26 IFD5XX Optional Ship Kits
Helicopter Ship Kit
850-00188-001 820-00113-000 820-00113-001 850-00188-003 850-00188-005
Component
IFD4XX Tray
Fixed Wing Aircraft Ship Kits
850-00184-000
IFD4XX Install kit (no tray) IFD440
820-00114-000
IFD4XX Install kit (no tray) IFD410
820-00114-001
IFD4XX Tray and Install Kit IFD440
850-00184-002
IFD4XX Tray and Install Kit IFD410
850-00184-004
Table 27 IFD4XX Optional Ship Kits
Helicopter Ship Kit
850-00184-001 820-00114-000 820-00114-001 850-00184-003 850-00184-005
Component
Ship Kit 850-00217-001
GPS Antenna
200-00282-000
Table 28 GPS Antenna Kit
Component
Ship Kit 820-00101-001
ByteFlight Cable, 20 ft. 033-00102-000
Table 29 ByteFlight Ship Kit
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1.13 Materials Required but not Supplied
The IFD5XX/4XX will require common installation supplies. The following items may be required for installation, but not supplied:
· Wire (Shielded and Un-shielded) · Hardware (Screws, washers, nuts, ring terminals, etc) · Circuit Breakers · Tie wrap or Lacing Cord · Coaxial Cables · Wire Splices · Solder Sleeves · Antenna(s) · Diplexers
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2. Installation Considerations
The following section will describe installation instructions for the IFD5XX/4XX Unit. The IFD5XX/4XX should be installed using standard industry practice while following guidance in FAA AC 43.13-( ), AC 20-138 ( ), and AC 20-67( ).
2.1 Plug & Play Considerations
The IFD5XX/4XX is designed to be a slide-in replacement for a GNS-530/W or GNS-430/W. For those replacement installations in fixed wing aircraft, the existing aircraft tray and wiring can all be reused. However, all electrical wiring, including power(s) and ground(s), should be verified per installation data shown in Appendix D: Electrical Interface Drawings. Note that 14v aircraft may be required to replace the installed circuit breaker and power and ground wiring to accommodate the IFD5XX/4XX.
If the unit being replaced was a WAAS-enabled device, then the WAAS antennas previously installed can be reused, assuming they are one of the GPS WAAS antennas identified in Section 3.3.5.
If the unit being replaced was not a TAWS-enabled device, or if the TAWS Audio output signals were not already connected to the aircraft audio panel(s), then some additional wiring will be required from the IFD5XX/4XX tray to the aircraft audio panel(s) as identified in Section 6.11.1 in order to supply IFD5XX/4XX terrain alerting audio (Forward Looking Terrain Alerting FLTA functionality) and TOD chime to the headsets.
For those installations that use a combined IFD5XX/4XX Avidyne AXP340/AXP322 Mode S ADS-B transponder, the on-ground/in-air discrete signal wire may need to be added from the IFD5XX/4XX tray to the AXP340/322 tray as identified in Section 6.12.
Note: Installations replacing an existing non-WAAS GPS/NAV/COM transceiver can upgrade to a WAAS installation using section 3 of this manual.
Note: Installations replacing a GNS-530/W or GNS-430/W must verify the aircraft is on the IFD5XX/4XX Approved Model List, Avidyne Document Number AVIFD-318.
Note: It is imperative that only one source of terrain cautions and warnings be enabled on the airplane so as to avoid the potential for conflicting information to be presented to the pilot. If a TAWS system is installed but the IFD's internal TA and FLTA functions are to be used for terrain avoidance, the TAWS system must be fully disabled. If a separate TAWS system is to be used the caution and warning indications generated by the TAWS system can be displayed on a remote third party annunciator and the IFD's TA and FLTA displays and audio must be inhibited. See section 7.5.4.
Note: If the unit being replaced was a TAWS-enabled device used for 91/135 TAWS compliance, the IFD5XX/4XX cannot be installed without a separately installed EGWPS/TAWS unit.
Avidyne TA/FLTA is not an approved TSO-C151 EGPWS unit.
Note: The IFD system supports a Honeywell KGP560/860 system with a remote third party annunciator only. All other external TAWS/EGPWS systems must be disabled if the internal TA and FLTA are to be operational on the IFD system.
All installations must verify the aircraft complies with either Section 2.4.1 or 2.4.2 after completing the IFD5XX/IFD4XX installation.
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2.2 Optional Installation Features
This section summarizes optional features that may require extra wiring.
Feature Audio Panel Aurals
Description
Allows IFD5XX/4XX produced aural alerts (e.g. FLTA terrain alerts, Top of Descent alerts, 500' callouts, etc) to be heard in the headsets.
Reference Section for Installation Details
Section 6.11.1
Transponder Support
Video In Radar display
Com Presets, Forward*
Com Presets Reverse *
Com Frequency Active-Standby Swap* Nav Frequency ActiveStandby Swap * Synchro Heading Input * Standby Com Monitor*
WiFi/Bluetooth
Allows IFD5XX/4XX GPS position transmission to the transponder for ADS-B operation and IFD5XX/IFD4XX Air/Ground output to the transponder for automatic Ground-Alt transition.
Allows input from any RS-170 format video.
Allows display of digital radar display. The IFD5XX can control the radar as a standalone display.
Enables external command (e.g. yokemounted button) to select frequencies forward in the com preset list to be loaded into the #1 Standby com slots.
Enables external command (e.g. yokemounted button) to reverse selected frequencies in the com preset list to be loaded into the #1 Standby com slots.
Enables external command (e.g. yokemounted button) to swap the Active and #1 Standby com frequencies.
Enables external command (e.g. yokemounted button) to swap the Active and #1 Standby nav frequencies.
Allows the IFD5XX/4XX to take heading data in via synchro protocol.
Allows the com frequency in the #1 standby slot to be heard in the headsets when installed with a compatible audio panel (e.g. Avidyne AMX240).
Allows the connection of portable electronic equipment to the IFD5XX/4XX.
IFD4XX/5XX
Enables the IFD4XX/5XX for use in helicopters
Helicopter Enablement
*N/A for IFD510/545/410
Section 6.12
Section 6.15 Section 6.16
Section 6.1.12.4
Section 6.1.12.4
Section 6.1.12.4
Section 6.1.12.4
Section 6.1.6 Section 6.1.12.5
Requires Ship Kit (Field load) 850-00179-501 KIT, IFDXXX WIFI BLUETOOTH ACTIVATION Reference Service Bulletins: 601-00182-020 SERVICE BULLETIN, ACTIVATION, IFD540 WIFI BLUETOOTH 601-00179-005 SERVICE BULLETIN, ACTIVATION, IFD440 WIFI BLUETOOTH Requires Ship Kit (Field load) 500-00258-001
Table 30 Optional Installation Features
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2.3 IFD5XX/4XX Interfaces
The IFD5XX/4XX can interface with a host of other avionics equipment. The following list represents the proven interfaces. There may be other devices that can be configured the same as one on the below list but Avidyne has not tested it and can therefore not make any compatibility claims.
Category
Vendor
Model
Air Data
B&D
2600 ADC
B&D
2601 ADC
B&D
2800 ADC
B&D
900004-003 ADC
Bendix King
KAD 280/480 ADC (KDC 281, 481)
Shadin
8800T Alt Computer
Shadin Shadin
Encoding Altimeter or Blind Encoders
EFIS
Shadin Insight Icarus Sandia Garmin Bendix King
Bendix King Terra Sandia Trans-Cal Industries Trans-Cal Industries ACK Technologies Bendix King Avidyne Aspen Collins Collins Honeywell Sextant
9000T Alt Computer 9200T Alt Computer 9628XX-X Fuel/Air Data Computer TAS 1000 ADC Instrument 3000 SAC7-35 GDC74A KEA-130A
KEA-346 AT-3000 SAE5-35 IA-RS232-X SSD120 A-30 EFS 40/50 EXP5000 Pilot PFD (EFD1000) Proline 21 EFIS 84 Primus 1000 SMD 45
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Category Displays
Heading EHSI
IFD5XX/4XX Installation Manual
Vendor Garmin Garmin Garmin Garmin Garmin Garmin Garmin Garmin Garmin Garmin Garmin Garmin Garmin Garmin Argus Argus Argus Horizon Avidyne Avidyne Avidyne Avidyne Bendix King
Collins Honeywell
Litef Litton Litton Litton Sandel Sandel
Model G500/600/TXi G5 MX20 GMX200 GPSMAP 195 GPSMAP 295 GPS III Pilot GPSMAP 196 GPSMAP 296 GPSMAP 396 GPSMAP 496 GPSMAP 695 GPSMAP 696 Aera 796/795 3000 5000 7000 DDMP EX500 EX600 EX5000 FlightMax Series KAH 460 Inertial System (KAU 461 also) AHC 85 Inertial System Laseref HG 1075AB, HG 1095AG Inertial Systems LTR 81 Inertial System LTN 90-100 Inertial System LTN 91 Inertial System LTN 92 Inertial System SN3308 SN3500
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Category Fuel
Traffic Transponder
IFD5XX/4XX Installation Manual
Vendor Shadin
Shadin
Shadin
JPI JPI JPI ARNAV ARNAV EI EI Insight L3 L3 Bendix King Bendix King Bendix King Bendix King Garmin Ryan Ryan Avidyne Garmin
Garmin Garmin Garmin Garmin Garmin Honeywell Bendix/King
Model 91053XP and 91053XT-D "Digiflo-L" Digital Fuel Mgmt Systems 91204XT(38)D and 91204XT-D "Miniflo-L" Digital Fuel Mgmt Systems 91802-() "DigiData" Fuel/Airdata EDM-700 Engine Monitor EDM-760 Engine Monitor FS-450 FC-10 FT-10 FP-5L CGR-30P GEM 3 SKY497 SkyWatch SKY899 SkyWatchHP KTA-870 KTA-970 KMH980 KMH880 GTS800/820/850 TCAD 9900B TCAD 9900BX TAS-6XXA series GTX330 (transponder functionality only) GTX330 ES * GTX 330D ES * GTX335 * GTX 345 * GTX 327 KT74
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Category
Lightning Datalink Autopilot
IFD5XX/4XX Installation Manual
Vendor L-3 Trig Rockwell Collins Avidyne L3 Avidyne Garmin Avidyne WSI Heads-up Technologies Avidyne Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Century Century Century Century Century Century Century Century Century
Model NGT9000 Series TT31/22 TDR94/TDR94D AXP340/322 WX500 TWX670 ("Native" format) GDL-69/69A*** MLB700/100 AV-300/350 XMD076 DFC90 KFC400 KCP320 KFC325 KFC300 KFC225 KFC200 KFC250 KFC275 KFC150 KAP150 KAP140 KAP100 I II III IV 21 31/41 2000 Triden AK 1081 GPSS Converter
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Category
Miscellaneous EGPWS DME
Nav Indicator
IFD5XX/4XX Installation Manual
Vendor Collins Collins Collins STec STec STec STec STec STec STec STec STec STec STec Garmin Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Collins Collins Collins Narco Narco ARC (Cessna) Garmin Garmin
Model APC-65 Series FGC-65 FYD-65 20 30 40 50 55 55X 60 PSS 60-1 60-2 65 ST901 GPSS Converter GAD42 Interface Adapter KGP560 KN 61 KN 62/62A KN 63 KN 64 KN65 KDI 572 KDI 574 KDM706 DME 40 DME 42 TCR 451 DME 890 IDME 891 RTA-476A GI 102/A GI 106/A
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Category
RMI External GPS Annunciator Remote TAWS Annunciator Audio Panel
Vendor Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King Century Century Collins Collins Collins Mid Continent Mid Continent STec Sperry Sperry Sperry Bendix King Bendix King Bendix King Mid Continent Staco Switch Vivisun Vivisun Garmin Mid Continent Avidyne
Model KI 202 KI 203 KI 204 KI 206 KI 208 KI 208A KI 209 KI 209A KI 525A KPI 552/B KPI 553/A/B NSD 360A NSD 1000 331A-6P 331A-9G PN-101 MD 222-402/-406 MD 200-20X/-30X ST 180 RD444 RD 550A RD 650 KI 229 KNI 582 KDA 692 MD41-Series 992561 95-40-( ) 95-45-( ) 013-0079-XX MD41-10XX AMX240
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Category
Vendor
Model
Apollo (Garmin)
SL10
Apollo (Garmin)
SL15
Garmin
GMA 340
Garmin
GMA 347
PS Engineering
6000
PS Engineering
7000
PS Engineering
8000/8000BT
Bendix King
KMA 24/24H
Bendix King
KMA 26
Bendix King
KMA 28
406 ELT
Artex
ME406
Ameri-King
AD 451-()
Ack
E-04
Narco
Not specified
Pointer
3000
Kannad
Not specified
Radar
Bendix King
RDR 2000 *
UAT
Avidyne
Skytrax100 (formerly MLB100)
Avidyne
SkyTrax100B*
Freeflight Systems
FDL-978-RX**
Garmin
GDL 88**
*IFD Software version 10.2 or higher
**IFD Software version 10.2.1 or higher *** Compatibility with P/N 011-00986-00 or 011-00987-00 only pre software 10.2.3.1. With software 10.2.3.1 or higher P/N 011-03177-X0 will function
Table 31 IFD5XX/4XX Compatible Equipment
2.4 Minimum System Configuration
The IFD5XX/4XX can be installed in one of two configurations.
2.4.1 VFR Installation
This section is intended for stand-alone IFD5XX/4XX installations intended for VFR navigation on un-pressurized aircraft less than 6000 pounds. The following items must be installed in IFD5XX/4XX VFR Configuration:
· IFD5XX or IFD4XX unit · GPS Antenna (TSO-C144a or TSO-C190, reference Section 3.3.5 for
approved antennas) · VHF Communication Antenna is needed for communication
functions (N/A for IFD510/545/410)
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· VHF Navigation Antenna is needed for VOR functions (N/A for IFD510/545/410)
All VFR installations must install a "GPS APPROVED FOR VFR USE ONLY" placard. All VFR installations, as described in this Section, are considered a minor alteration when installed on a no-hazard basis to supplement VFR navigation.
2.4.2 IFR Installation
This section is intended for IFR installations. The following items must be installed in IFD5XX/4XX IFR Configuration:
· IFD5XX or IFD4XX unit;
· GPS Antenna (TSO-C190 or approved antennas listed in Section 3.3.5)
· VHF Communication Antenna is needed for communication functions; (N/A for IFD510/545/410)
· Navigation Antenna(s) is needed for VOR/LOC/GS functions; (N/A for IFD510/545/410)
· Remote Annunciator is required if the IFD5XX/4XX is not in the field of view of the pilot, reference Section 5.1.2;
· IFD5XX/4XX should be interfaced to an Airdata source for automatic altitude leg sequencing (optional). If no baro-altitude data is supplied, altitude leg types must be manually sequenced for IFD5XX with Software 10.0.3.0 or earlier.
· The IFD5XX/4XX must be connected to an external CDI/HSI/EHSI indicator installed in the pilot's field of view. The CDI must have a Vertical Deviation Indicator;
· Second navigation receiver or communication transceiver must be installed on all multi-engine or turbine-powered aircraft with a gross takeoff weight greater than 6000 lbs. Aircraft using GPS Oceanic/Remote navigation must have a second navigation receiver installed in the aircraft. In both cases, the second navigation receiver or communication transceiver must be a FAA TSO'd unit.
· Separately approved Marker Beacon System.
All aircraft approved for GPS Oceanic/Remote navigation must have dual electrical power/ground connections to both IFD5XX/4XX units as shown in Section 4.9 and described in FAA AC 20-138( ) Appendix 1.
Figure 1 shows an IFR installation. IFR installation must be installed as major alteration to the aircraft.
Note: All equipment required by 14 CFR 91.205 must be previously installed on the aircraft for IFR operations.
If the IFD54XX/4XX is installed per this section, it can provide guidance for the following operations conducted under instrument flight rules (IFR):
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· VOR, LOC, ILS instrument approach procedures (procedures using VHF radio guidance)
· RNP instrument approach procedures using the following lines of minima: o LNAV minima (including when using advisory vertical guidance from the system); o LNAV/VNAV minima; o LPV minima; and o LP minima.
Air Data/ Heading Data
Autopilot Datalink (WSI, XM, etc.) Lightning Detection
Traffic System
Transponder Fuel
Management System
ELT
EGPWS
Encoding Altimeter
600-00299-000
Avidyne IFD5XX/4XX GPS/Nav/Comm
Audio Panel
CDI/HSI
DME
EFIS/MFD
Switches/ Annunciators
NAV Antenna
Com Antenna
GS Antenna
GPS Antenna
CrossSync to 2nd IFD
Figure 1 Full IFR Installation (IFD5XX/4XX)
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2.5 Pre-Installation Checklist
Prior to beginning installation of the IFD5XX/4XX, complete the following pre-installation checklist. This checklist will help in determining installation requirements. If the Installation Items below are not complete, additional installation approval may be required.
Installation Item
Reference
Is the aircraft on the Avidyne STC Approved Avidyne Document
Model List?
AVIFD-306
Is IFD5XX/4XX replacing an existing GPS/NAV/COM used for Part 91/135 TAWS compliance?
If yes, a separate TAWS system must be installed.
(Ref. Section 2.1)
Can the IFD5XX/4XX tray be installed per the data in this manual?
If No, additional installation approval is required.
Navigation(s) Antenna Installed
Section 3.5
(N/A for IFD510/545/410)
Communication Antenna Installed
Section 3.4
(N/A for IFD510/545//410)
Is the IFD5XX/4XX, or remote annunciator lights, installed within the Pilot's Field of View?
Section 5.1 or 5.2
Does the aircraft have an approved GPS antenna installed on the aircraft? Or, can the GPS antenna be installed per this manual?
Section 3.3.5
Does the aircraft have a previously approved Section 2.4.2 Marker Beacon System installed in the aircraft? (Not needed for VFR installations)
Does the aircraft have a second NAV or COMM installed?
Section 2.4.2
Does the aircraft have a sufficient electrical power for the IFD5XX/4XX installation?
Section 1.5
Does the installation location comply with the Environmental Testing of the IFD5XX/4XX unit?
Appendix A: Environmental Qualification Form
Does the Airplane Flight Manual Supplement adequately cover the installation?
If no, additional installation approval is required. (Reference: Avidyne Document 600-00298-000 or 600-00305-000)
IFD5XX
Table 32 Pre-Installation Checklist
IFD4XX Complete
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3. Antenna Installation
This section describes the installation of the GPS, NAV, and Glideslope antennas on unpressurized, metallic fuselage airplanes. The installer is responsible to ensure the structural aspects of the installation meet all regulatory requirements and are adequate for the aircraft type. Antenna installations on airplanes with composite or pressurized fuselages, and aircraft with certification basis of Amendment 23-45 or later, are beyond the scope of this manual and a separate installation approval is required.
3.1 Antenna Bonding
All antennas should be well bonded to the aircraft. Reference AC 43.13-2b paragraph 307 for additional information.
3.2 Antenna Environmental Qualifications
Verify the antenna is appropriately qualified to be installed on the aircraft. Reference the antenna manufacturer's RTCA DO-160(x) qualification form.
3.3 GPS Antenna
The GPS Antenna should be installed using practices acceptable to the antenna and aircraft manufacturers. Regulatory guidance for antenna installations can be found in AC 20-138( ) Chapter 12, AC 43.13-2B Chapter 3, and AC 43.13-1B Chapter 4. Also reference Appendix C in this manual.
The GPS antenna listed in Table 28 can be installed on unpressurized metal airplanes with a certification basis of Amendment 23-43, or earlier, using the data below. All other GPS Antenna installations are beyond the scope of this manual and a separate installation approval is required.
The Avidyne GPS antenna, Avidyne Part Number 200-00282-000, can be installed as shown in Figure C - 5 through Figure C - 9. The GPS Antenna must be installed using the following guidelines to be in compliance with the STC.
GPS Antenna Location: · Fuselage skin must be 2024-T3 aluminum (or equivalent) · Fuselage skin thicknesses beyond the range provided in Table 33Table 33 below are outside the scope of this installation · Selected antenna location may not be within one full bay of other cutouts, skin joints, or load introduction points · Doubler installation on, or adjacent to, primary or fatigue critical structure, as defined by the aircraft manufacturer or regulatory guidance, requires separate approval · Evaluate the installation per AC43.13-2B, Chapter 3, paragraph 303(b) for gaps due to fuselage curvature. If a saddle is required, fabrication should be per AC 43.13-1B, and should completely fill the curvature gaps, and should not be riveted to the fuselage skin. The only purpose of the saddle is to act as a tapered shim and is not intended to transfer load into the skin
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Doubler Fabrication: · Doubler material is to be 2024-T3 clad aluminum per AMS QQ-A-250/5 · Form the doubler to match the fuselage curvature · Etch, alodine, and prime the doubler per the guidance provided in AC43.13-1B · Drill holes and install rivets per AC43.13-1B o It is acceptable to slightly vary the rivet and row spacing to accommodate existing frames and stringers provided 2D edge distance and 4D minimum rivet spacing is maintained and no rivet is installed within 0.75" of the antenna mounting holes o Rivet type is dependent on the type of rivets in the adjacent fuselage structure. If the adjacent rivets in the structure around the bay selected for the doubler installation are protruding head type, install MS20470AD rivets in the outer row of the doubler. If the adjacent rivets are countersunk or dimpled, install either MS20426AD or NAS1097AD rivets per the table below. Reference Table 124 for rivet type and doubler thickness appropriate for the aircraft's skin thickness.
Fuselage Thickness 0.016-0.025" 0.032-0.050
Doubler Thickness 0.020" 0.032"
Table 33 Doubler Thickness
Doubler Drawing
See Figure C - 8 in Appendix C.
3.3.1 GPS Location
The following recommendations should be followed when choosing an installation location for the GPS antenna. Prior to installing the GPS antenna, it is recommended to temporarily mount the GPS antenna in the desired location and functional ground test the GPS system.
· The antenna must be mounted on the exterior upper fuselage of the aircraft
· The GPS antenna should be mounted more than 2 feet from any transmitting antenna.
· The GPS antenna should be mounted in a location that minimizes the effects of shadowing by the aircraft structure.
· The GPS antenna should be installed more than 6 inches from any other antenna, including another GPS antenna.
· The GPS antenna should be installed in a location that allows the antenna to be level in normal cruise flight.
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· For multiple GPS installations, the antennas should not be mounted in a straight line from front to rear of the aircraft along the longitudinal axis on the aircraft to prevent simultaneous antenna damage from lightning strikes.
· Antennas should be installed 3" or more from the windshield.
3.3.1.1 Aircraft Lightning Zone
If installing an Avidyne GPS Antenna (Avidyne Part Number 200-00282-000), the GPS antenna is qualified to be installed in aircraft lightning zone 2A as defined by SAE ARP5414A and RTCA DO-160G. The No Installation Area can be determined using Figure 2. The distance found by using Figure 2 defines a zone immediately aft of the nose of the aircraft, or propeller in the case of single engine propeller driven aircraft, where the GPS antenna should not be installed. Aircraft locations aft of the No Installation Area are acceptable to install the GPS antenna. Figure 3 below shows an example of the No Installation Area.
Figure 2 Distance to Aircraft Lightning Zone 2A
Procedure:
1. Determine the Maximum Cruising Speed (Vno) for the aircraft. Note: Indicated Airspeed in knots (KIAS) must be used in the table.
2. Locate the Airspeed for the aircraft on the Horizontal Axis of the table. Draw a vertical line from the Airspeed to the No Installation Area.
3. Draw a horizontal line from the No Installation Area, found in Step 2, to the Vertical Axis on the chart.
4. Determine the Distance (in feet) to Aircraft Lightning Zone 2A for the aircraft on the Vertical Axis.
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Example: For example, if an aircraft shown in Figure 3 has a Vno of 175 KIAS, the No Installation Area will be 7.2 feet. This is shown on Figure 2 with a dotted line and Figure 3 with a shaded area. Aircraft with a Vno greater than 210 KIAS may install the GPS antenna 8.6 feet aft of the nose of the aircraft (excluding propeller).
Figure 3 Aircraft No-Installation Area
Note: Locating the GPS antenna in the correct aircraft lightning zone is the responsibility of the installing agency. If a System Equipment DER is necessary, the Aircraft Electronics Association is a good source of information. The telephone number is +1 (816) 347-8400.
3.3.2 GPS Antenna Bonding
The GPS Antenna should have 2.5 milliohm resistance to the aircraft fuselage.
3.3.3 GPS Antenna Cable
The GPS Antenna Cable must be RG-142B, RG-400, or an equivalent 50 double shielded coaxial cable. The GPS antenna cable loss should not be greater than 6.5dB or less than 1.5 dB. Each connector on the GPS coaxial cable will add an additional 0.2 dB loss to the cable. The GPS antenna cable should not be routed with high power wires or transmitting antenna cables. If dual GPS Systems are installed on the aircraft, the GPS coaxial cables should be routed in such a manner to provide maximum separation between the two GPS coaxial cables.
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3.3.4 GPS Coaxial Cable Connector
The connectors on the GPS coaxial cable should be assembled per the connector manufacturer's assembly instructions.
3.3.5 Approved GPS Antennas
Model Number
Description
Supplier
CI-428-200
GPS WAAS Antenna
Cobham (Comant)
CI-2580-200
VHF/GPS WAAS Antenna
Cobham (Comant)
CI-2728-410
VHF/GPS/XM Antenna
Cobham (Comant)
GA-35
GPS/WAAS Antenna
Garmin
GA-36
GPS/WAAS Antenna
Garmin
GA-37
GPS/WAAS Antenna
Garmin
GA-56A
GPS/WAAS Antenna
Garmin
GA-56W
GPS/WAAS Antenna
Garmin
GA-57
WAAS/XM Antenna
Garmin
A33 (AT575-9UW)
A34 AV-801 AT575-93AVW-TNCF000-RG-27-NM
GPS/WAAS Antenna GPS/WAAS Antenna GPS/WAAS Antenna
GPS/WAAS Antenna
Garmin /AeroAntenna
Garmin /AeroAntenna RAMI
AeroAntenna Technology
Table 34 Approved GPS Antennas for SBAS Operation
The IFD5XX/4XX can be interfaced to all TSO-C190 antennas and the approved antennas listed in the table above. If connected to an approved WAAS Antenna, the IFD5XX/4XX is approved for TSO-C146d Gamma 3 operation.
The IFD5XX can be interfaced to non-WAAS antennas but the system will not be approved for any type of WAAS operations. In this case, the Antenna Type selection as described in Section 7.5.11 must be selected as "Non-WAAS". This will result in the FMS functionality of the IFD5XX/4XX inhibiting selection of any WAAS (SBAS) approach in the database.
Installing a new GPS antenna listed in Table 34 requires additional structural approval beyond the scope of this manual.
3.3.6 GPS Interference
After installing the IFD5XX/4XX System, the GPS antenna must be tested to insure no interference is present. The GPS Antenna System is subject to interference from VHF COM
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transceiver, Emergency Locator Transmitter (ELT) antenna, or Direction Finder (DF) receiver which can radiate harmonics that can potentially interfere with the GPS antenna. If a VHF Communication transceiver is found to be the problem, installing a 1.57542 GHz notch filter may help to reduce the problem.
3.3.7 Ground Plane
The GPS Antenna should be mounted on a minimum of 8 x 8 inch metal surface or ground plane.
3.3.8 Dual IFD5XX/4XX Installations
If the aircraft has dual IFD5XX/4XX, the aircraft is permitted to have a non-WAAS system and a WAAS system installed, however, if the two antennas are not of the same type (i.e. dual non-WAAS or dual WAAS installation), then FMS-related data (flight plans, waypoints, routes, etc) will not be shared between IFDs.
3.3.9 Anti-Ice Protection
If the aircraft is approved for flight into known icing, verify the GPS antenna is installed in location that is not susceptible to ice buildup or complies with FAA AC 20-138( ) paragraph 13-2.
3.4 VHF Communication Antenna
Note: This section is N/A for the IFD510/545/410. The VHF communication antenna should be installed using this manual, FAA AC 43.13-( ), AC 20-67B and the antenna manufacturer's guidance. The antennas should be installed to allow maximum separation between antennas. If possible, one antenna should be installed on the top of the aircraft, and the other on the bottom of the aircraft.
3.4.1 Antenna Environmental Qualifications
Verify the antenna is appropriately qualified to be installed on the aircraft. Reference the antenna manufacturer's RTCA DO-160(x) qualification form.
3.4.2 VHF Communication Cable
The antenna cable should be RG-142B, RG-400, or an equivalent 50 coaxial cable.
3.4.3 VHF Coaxial Cable Connector
The connectors on the VHF communication coaxial cable should be assembled per the connector manufacturer's assembly instructions.
3.4.4 Voltage Standing Wave Ratio
The VSWR should not exceed 2:1 over the VHF communication radio frequency range. A VSWR over 2:1 may result in loss in transmitting power up to 50%.
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3.4.5 VHF Antenna
The VHF Communication Antenna should meet one of the following Technical Standard Orders (TSO): TSO-C37( ), TSO-C38( ), TSO-C169( ).
3.4.6 Antenna Ground Plane
The VHF Communication Antenna should be mounted on a minimum of 18 x 18 inch metal surface or ground plane.
3.5 Navigation Antennas
Note: This section is N/A for the IFD510/545/410.
3.5.1 VOR/LOC Antenna
The NAV Antenna should be a standard 50 horizontally polarized antenna. The VOR/LOC antenna should be installed using the manufacturer's installation instructions and FAA AC 43.13-( ). The VOR/LOC Antenna should meet Technical Standard Order (TSO): TSO-C36 ( ), TSO-C40 ( ).
3.5.2 Navigation Coaxial Cable
The antenna cable should be made of RG-142B, RG-400, or an equivalent 50 coaxial cable.
3.5.3 Navigation Coaxial Cable Connector
The connectors on the VHF navigation coaxial cable should be assembled per the connector manufacturer's assembly instructions.
3.5.4 Diplexer
The IFD5XX/4XX requires separate Glideslope and Navigation antenna inputs. A diplexer will be required if a single navigation coax delivers both VHF navigation and Glideslope navigation signals to the IFD5XX/4XX location, such as if a combined Nav/Glideslope antenna is used, or a Nav/Glideslope diplexer is installed to combine signals at the antenna location. The diplexer should be installed per the manufacturer's installation manual. The Diplexer should be located in a position on the aircraft to minimize the amount of coaxial cable required.
3.6 Glideslope Antenna
Note: This section is N/A for the IFD510/545/410. The Glideslope Antenna should be standard 50 horizontally polarized antenna. The Glideslope antenna should be installed using the manufacturer's installation instructions and FAA AC 43.13-( ). The IFD5XX/4XX has separate VOR/LOC and Glideslope antenna inputs. See Diplexer text in Section 3.5.4.
3.6.1 Glideslope
The Glideslope Antenna should also be installed with a clear line of sight. The Glideslope Antenna should meet Technical Standard Order (TSO): TSO-C34( ).
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4. Electrical Installation
The electrical wiring should be installed in accordance with FAA AC 43.13-1B Chapter 11, sections 8 through 13 and in accordance with this manual. The following section will describe requirements for the electrical wiring when installing the IFD5XX/4XX.
4.1 Wire Type
MIL-C-27500 and MIL-W-22759 wire is recommended. Select the appropriate wire type and size for the aircraft type and installation location per FAA AC 43.13-1B.
4.2 Wire and Connector Identification
Wires and connectors should be marked per FAA AC 43.13-1B.
4.3 Wire Routing
All wires and wire bundles must be routed and secured in such a way to eliminate risk of mechanical damage and minimize exposure to heat and fluids. Also, consider the following when installing wire harnesses in the aircraft:
· In dual GPS installations, route wire harnesses separately to prevent dual GPS failures
· Do not route harness near high power electrical lines · Equipment should be installed with separation between redundant systems to
prevent loss of navigation due to a single event
4.4 Shield Grounds
All shield grounds should be grounded using the ground block on the IFD5XX/4XX tray backplate. Shield grounds should be as short as possible (shorter than 3.0", if possible) Shield grounds on non-Avidyne equipment should be grounded per the manufacturer's installation instructions. In the absence of any installation data, the shield wires can be connected to the connecter backshell or aircraft ground.
4.5 Wire Harness Overbraid
Copper overbraid is not required on the IFD5XX/4XX wire harness. However, in the following cases, copper overbraid is required.
4.5.1 Existing Equipment
If interfacing to any existing avionics equipment with copper overbraid over the wire harness, it must be installed on all new wiring to that existing piece of equipment. The copper overbraid must meet the specification in Section 4.5.3.
4.5.2 Severe Lightning Transient Environment
Aircraft Installations where the aircraft actual transients level is higher than the IFD5XX/4XX equipment transient design level must install copper overbraid on the entire IFD5XX/4XX wire harness. This does not include the antenna coaxial cables. The copper overbraid must be installed per Section 4.5.3.
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The Approved Model List for the STC will indicate if an aircraft is required to install wire harness overbraid on the IFD5XX/4XX wiring. Note: Overbraid is not required on VFR only installations as defined in Section 2.4.1.
4.5.3 Copper Overbraid Installation
The copper overbraid must be a minimum 90% optical coverage per ASTM-B-33. The overbraid must be grounded at both ends. If the aircraft wiring passes through wire disconnects or bulkheads, the overbraid should be continued on each segment.
The wire harness overbraid should also be installed per FAA AC 43.13-1B Chapter 11-189.
4.6 IFD5XX/4XX Connectors
The following special tools may be needed during installation of the IFD5XX/4XX:
Connector Connector Number Part number
Contact Part Numbers
Crimp Tool
Die/
Positioner
Extraction Tool
P1001 P1002
M24308/4- 268( ) M24308/2-3( )
M39029/58-360
(ORG/BLU/BLK)
M39029/63-368 (ORG/BLU/GRY)
M22520/02-01 M22520/02-01
M22520/2-09 M22520/2-08
M81969-1-04 M81969/1-02
Insertion Tool
M81969/1-04
M81969/1-02
P1006
P1050
Ground Block
M24308/4- 266( ) M24308/4- 268( )
M39029/58-360 (ORG/BLU/BLK)
M39029/58-360 (ORG/BLU/BLK)
M22520/02-01 M22520/02-01
M22520/2-09 M22520/2-09
M81969-1-04 M81969-1-04
M81969/1-04 M81969/1-04
583861-7 (TE Connectivity)
5-583853-4 (TE Connectivity)
91535-1 (TE Connectivity)
91073-1 (TE Connectivity)
Table 35 D-Sub Connector Tools
Please note: The P1050 is available on the IFD5XX Series only.
4.7 Byteflight Digital Data Bus Consideration Dual IFD Installations
Dual IFD installations use a Byteflight digital Databus protocol when connected via RS-232 Channel 3 and configured for CrossSync. The following must be considered for replacement and new installations.
4.7.1 Databus Wiring - Replacement Installations
For installations that are replacing two previously connected GNS4xx/5xx systems, the Byteflight digital Databus is capable of using the pre-existing wiring between the two preexisting trays with no additional wiring or modifications required. All bus termination is built into the IFD units. However, the existing wire length on the CrossSync connection must not exceed 8 feet in length on IFD5XX/4XX RS-232 Channel 3 on P1001. Installations with longer installation lengths between IFD5XX/4XX units must use Byteflight cable. The ByteFlight wire is available from Avidyne, reference Table 29.
Installations with significant amount of Byteflight data interruptions should consider installing Byteflight cable.
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4.7.2 Databus Wiring New Installations
For all new installations of dual IFDs (not replacing pre-existing GNS4xx/5xx systems), the recommended wiring for the RS-485 data protocol is shielded twisted- pair cable with an approximate characteristic impedance of 100-120 Ohms. The wire material must meet 14 CFR 23.1359 (c).
4.8 Circuit Protection
Circuit Breakers must be installed in a location easily accessible to the pilot and must be resettable trip free devices. The Circuit Breaker must be clearly identified and visible under all lighting conditions. Circuit breaker size is identified in installation data shown in Appendix D: Electrical Interface Drawings. Note that 14v aircraft may be required to replace the installed circuit breaker and power wiring to accommodate the IFD5XX/4XX.
4.9 Power Distribution
Note: The references in the below images to the COM block are N/A for the IFD510/545/410. Aircraft installing one IFD5XX/4XX should connect the power and grounds as shown in Figure 4.
Single Avionics Bus
Avionics Bus
IFD540/440
COM
Aircraft Ground
Figure 4 IFD5XX/4XX Power Distribution
Aircraft with a maximum certified gross takeoff weight less than 6000 pounds must connect the dual IFD5XX/4XX as shown in Figure 5.
Preferred
Alternate
Avionics Bus 1
Avionics Bus 2
Avionics Bus
IFD540/440
COM
IFD540/440
COM
IFD540/440
COM
IFD540/440
COM
Aircraft Ground
Aircraft Ground
Aircraft Ground
Figure 5 Dual IFD5XX/4XX Power Distribution (Aircraft <6000 lbs)
Aircraft Ground
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Aircraft with a maximum certified gross takeoff weight greater than 6000 pounds must install the dual IFD5XX/4XX as shown in Figure 6.
Preferred
Avionics Bus 1
Avionics Bus 2
Alternate
Avionics Bus
Main Bus
IFD540/440
COM
IFD540/440
COM
IFD540/440
COM
IFD540/440
COM
Aircraft Ground
Aircraft Ground
Aircraft Ground
Figure 6 Dual IFD5XX/4XX Power Distribution (Aircraft >6000 lbs)
Aircraft Ground
If installing a 3rd party NAV and/or COM and IFD5XX/4XX, connect the IFD5XX/4XX as shown in Figure 7.
Preferred
Alternate
Avionics Bus 1
Avionics Bus 2
Main Bus
Avionics Bus
IFD540/440
COM
Other COM/NAV
IFD540/440
COM
Other COM/NAV
Aircraft Ground
Aircraft Ground
Aircraft Ground
Aircraft Ground
Figure 7 Dual NAV/COM Aircraft Bus Installation (Aircraft >6000 lbs)
The installer is responsible for preservation of multiple power busses on the aircraft in accordance with manufacturer's original design and the requirements of 14 CFR Part 23. This includes maintaining electrical power to essential equipment.
4.10 Electrical Load Analysis
Prior to installing the IFD5XX/4XX, an electrical load analysis (ELA) must be performed. The aircraft's electrical load should be less than 80% of the total generator output following the IFD5XX/4XX installation, reference Section 1.5 for IFD5XX/4XX power requirements. Also reference FAA AC 43.13-2B Paragraph 208 for more information on performing an aircraft electrical load analysis.
The purpose of the ELA is to show compliance to 14 CFR §23.1351 and §23.1353 (h).
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4.11 Low Power Behaviors
The IFD5XX/4XX can accept input power ranging from 9VDC to 33VDC but has the following low power behaviors.
Functions are restored if the IFD input voltage rises 1VDC above threshold voltage for 1 second.
Input Voltage Level
Behavior
19.9VDC
16W VHF radio output power reduces to 10W *
18VDC
High power USB charging (dedicated charging port drawing 2.1A).
< 18VDC
USB port drops from High power USB charging to Low power USB charging (dedicated charging port drawing 1.0A).
12.75VDC
USB port is turned off (no charging available).
11.5VDC
Bezel and LCD display dimmed down to 25% and a yellow "Low Volts" CAS message is presented.
10.9VDC
VHF radio output power reduces to 6W *
10.0VDC
VHF radio output power reduces to 4W *
9VDC
Start a 60 second power down sequence and a red "Low Volts Off in <x> sec" CAS message is presented. With 5 seconds to go until power down, the full power down message is overlaid in the middle of the display.
*N/A for IFD510/545/410
Table 36 IFD5XX/4XX Low Power Behavior
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5. Mechanical Installation
This section will describe the physical mounting of the IFD5XX/4XX in the aircraft.
Aircraft installing the IFD5XX/4XX for VFR use only, as defined in Section 2.4.1, can install the IFD5XX/4XX unit in any location easily accessible to the pilot. However, the IFD5XX/4XX installation must not introduce any new hazards. All other installations must follow the guidance below.
5.1 Equipment Location New Installations
If the IFD5XX/4XX is used for IFR navigation, course deviation information and navigation annunciation must be installed in the Pilot's Field of View (FOV). The FAA has provided clarification regarding the intent of TSO-C146 and acceptable source annunciation location, navigation annunciation, and FOV requirements on similar products in the past. Therefore, the installation data as follows must be followed to maintain compliance with the STC. Otherwise, additional installation approval will be required.
Aircraft requiring two pilots must have this annunciation at each pilot station or unobstructed view of the IFD5XX/4XX display. The IFD5XX/4XX should be located in a position easily reached by both pilots.
5.1.1 Determining the Field of View
The navigation source selection ("GPS" or "VLOC") field of view is approximately ±30° or 13.856" horizontally from the center of the attitude indicator, or centerline of the pilot's seat/yoke. The navigation annunciation field of view is approximately ±35° or 16.805" horizontally from the center of the attitude indicator. Both of these angles and distances are determined with the pilot seated at a minimum of 24" from the instrument panel. For aircraft without a basic instrument 'T' or an offset control yoke/control, use the center of the pilot's seat as the primary view centerline.
The vertical field of view will be from the top of the instrument panel to the portion of the instrument panel that is immediately below the basic 'T' instruments, reference Figure 8. Note, if the existing type certified HSI/CDI/PFD is lower than the basic 'T', use that as the lower limit.
Figure 8 below indicates the acceptable field of view for the IFD5XX/4XX. If the IFD5XX/4XX can be installed in this area, remote navigation annunciation is not required. If the IFD5XX/4XX cannot be installed within the acceptable field of view, the installation must have navigation annunciations installed per Section 5.1.2.
Note: The dimensions shown in Figure 8 and Figure 9 for the IFD5XX also apply to the IFD4XX.
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Figure 8 Field of View
5.1.2 Navigation Annunciation
The navigation annunciations listed in Table 37 must be installed in the Pilot's Field of view. This may be accomplished in several ways. The following are acceptable:
· Use Navigation Annunciation on an existing Primary Flight Display or Horizontal Situation Indicator located in the Pilot's primary field of view. CDI/HSI indicators with navigation annunciation is acceptable (e.g. GI 106, MD200306, or similar). The CDI/HSI must be located within the primary field of view.
· If the IFD5XX/4XX is located within the acceptable field of view, as shown in Figure 8, external annunciation is not needed
· Install external annunciation lights in the acceptable field of view, as shown in Figure 9.
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The IFD5XX/4XX should have the following annunciation within the Pilot's Field of View when installing an external annunciator:
Navigation Annunciation Type VLOC Annunciate GPS Annunciate
OBS Annunciate (optional) Waypoint Annunciate Terminal Annunciate Approach Annunciate Message Annunciate
LOI, INTEG, or INTG Annunciate
Table 37 Navigation Annunciation
Must be located ±30° or 13.856", see Section 5.1.1 The navigation annunciators should be readable under all lighting conditions. The annunciators must be able to be tested prior to flight. The field of view in Figure 8 is based on ±35° from the Instrument "T" centerline at 24" aft of the panel.
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Figure 9 Navigation Annunciation Field of View
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5.1.3 Course Deviation Indicator
The course deviation information must be located in the Pilot's Primary Field of view if the IFD5XX/4XX is used for IFR navigation. Installation of a CDI/HSI requires a separate installation approval.
5.1.4 Instrument Panel Cutout
The IFD5XX and IFD4XX tray is designed to be installed on the backside of the instrument panel. The instrument panel requires either a 6.320" x 4.600" or 6.320" x 2.70" hole for the IFD5XX or IFD4XX respectively. If the instrument panel in the aircraft is considered primary structure, additional installation approval will be required for the instrument panel cutout. The installer is responsible to ensure the structural aspects of this installation meet the requirements of AC 43.13-2B, Chapter 11, Paragraph 1104(a).
5.1.5 Requirements for Tray Installation
The Avidyne Tray must be installed in the aircraft as described below in order to satisfy the structural requirements for the STC. Deviations to these requirements will require separate approval.
1. Rear Tray Support (Instrument Panel)
a. The existing instrument panel must be fabricated from 2024T3 aluminum with a minimum thickness of 0.050". The tray brackets must be fabricated from 3/4" x 3/4" x 1/16" 2024-T3 aluminum angle extrusion for mounting the tray, as shown in Figure C - 1 and Figure C - 2.
b. If new components are fabricated, the fabrication methods must follow the requirements of FAA Advisory Circular 43.13-1B, Chapter 4 for general airframe fabrication criteria, including hole tolerances, edge distances, rivet spacing, and corrosion protection, and Advisory Circular 43.13-2B Chapters 2 and 11 for structural adequacy.
2. Forward Tray Support
a. The Avidyne Tray must have forward support brackets, reference Figure C - 1 or Figure C - 2. The forward support brace must be 0.032" 5052-H32 aluminum. (Note: equivalent or stronger is acceptable)
b. If new forward support brackets are fabricated, the fabrication methods must follow the requirements of either Figure C - 1 or Figure C - 2, FAA Advisory Circular 43.131B, Chapter 4 for general airframe fabrication criteria, including hole tolerances, edge distances, rivet spacing, and corrosion protection, and Advisory Circular 43.13-2B, Chapters 2 and 11 for structural adequacy.
The IFD5XX should be installed using six #6-32 flat head screws and self locking nuts. The IFD4XX should be installed using four #6-32 flat head screws and self locking nuts.
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5.2 Equipment Location - Replacement Unit
If the IFD5XX/4XX is being installed as replacement unit on a previously approved IFR installation, the existing installation location is acceptable and does not require any changes.
5.3 Angle of Regard
The IFD5XX/4XX should be mounted in a location where the viewing angle of the display does not exceed the following angles:
· From the Left: 45°
· From the Right: 45°
· From the Top: 35°
· From the Bottom: 35°
5.4 Unit Installation/Removal
The IFD5XX/4XX should be installed using 3/32-inch hex drive tool. The hex drive is inserted into the hole in the front bezel.
5.5 Internal Cooling
The IFD has several internal fans and heat sinks as part of its basic design. There are exhaust vents on the left and right sides of the chassis with cut outs in the tray to facilitate venting. The left and right side of the front bezel have intake louvers to help pull ambient cockpit air through the unit. While not necessary, if installation flexibility permits, the unit will benefit from these intake and exhaust vents remaining as clear as feasible.
5.6 External Cooling
The IFD5XX/4XX does not require external cooling, however, additional cooling may prolong product life. A 5/8" diameter air fitting is provided in the rear of the IFD5XX/4XX mounting tray, if forced air cooling is installed.
IFD5XX/4XX installations in a tightly packed avionics stack should consider installing an electric avionics cooling fan. As a minimum, plan to leave space for clear intake and exhaust venting when able. If a fan is installed, ensure the intake air flow to the fan is not located near the exhaust of other fans or near other hot equipment.
In the event the system feels excessively hot or if an Overtemp Caution Advisory System message is presented on the display, there are some diagnostic tools provided in the IFD5XX/4XX to assist in finding more optimal cooling installations. In Maintenance Mode, select the "Status" tab along to bottom edge of the display and then press the "Info" Line Select Key as needed until "Temps" is displayed. Note the hottest source(s) on that page and supply that information to Avidyne Technical Support to include both the source and the associated temperature for follow-on guidance.
The metal bezel of the IFD5XX/4XX is intentionally designed to radiate heat away from the internal components and out of the unit. This can have the effect of a bezel that may be warm to the touch. This is considered normal. Note that the rubber bezel buttons will not conduct this heat and should not be warm. This condition will be more noticeable on hot days or during long ground runs.
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5.7 Electrical Bonding
The electrical bonding between the IFD5XX/4XX tray and aircraft ground should be 10 milliohm.
5.8 Aircraft Considerations
Installing wires or antennas on a pressurized aircraft, composite aircraft, or with an aircraft certification basis of Amendment 23-45 or later is beyond the scope of this manual and requires additional installation approval, unless the aircraft model is listed on the STC AML.
5.9 Weight and Balance
After installing the IFD5XX/4XX, the aircraft's weight and balance must be updated after installation is complete. For those installations where an IFD540/545/440 is replacing a GNS530/430 (any variant), since the IFD540/545/440 is within 5% of the weight of the removed GNS530 (less than 1 pound difference), no new weight and balance must actually be performed according to AC 43.13-1B Change 1 Acceptable Methods, Techniques, and Practices Aircraft Inspection and Repair (Chapter 10) and AC 120-27E Aircraft Weight and Balance Control.
5.10 Compass Safe Distance
The IFD5XX/4XX should be installed 12" or more away from the aircraft's magnetic compass. Perform an aircraft compass swing/calibration after completing the IFD5XX/4XX installation. Note: The 12" minimum distance is a TSO-driven value that is designed to ensure the unit will have no impact on the aircraft compass. If an installation is made where this distance is less than 12", then a compass swing/calibration must be accomplished after completing the IFD5XX/4XX installation.
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6. System Installation
The following section will describe interfacing the IFD5XX/4XX to various other avionics and aircraft equipment.
6.1 Pin Function List
The following Section Lists the Pin function for each connector.
6.1.1 P1001 Main Connector
Pin
Description
1 VLOC Annunciate
2 GPS Annunciate
3 Waypoint Annunciate
4 Terminal Annunciate
5 Approach Annunciate
6 Message Annunciate
7 OBS Annunciate
8 Weight on Wheels (WOW) Output
9 Integrity Annunciate
10 Annunciate D
11 Annunciate E
12 Reserved
13 GPS Select
14 ILS/GPS Annunciate (Approach)
15 Aircraft Power 2
16 Time Mark Out
17 Main Lateral Superflag
18 Main Vertical Superflag
19 Aircraft Power 1
20 Aircraft Power 1
21 Main +Left
22 Main +Right (1.65V COM)
23 Main Lat +Flag
24 Main Lat -Flag (GND)
25 Main +To (1.65V Common)
Signal Type Output Output Output Output Output Output Output Output Output Output Output Output Output Output Input Output Output Output Input Input Output Output Output Output
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Pin
Description
26 Main +From
27 Main +Up (1.65V Common)
28 Main +Down
29 Main Vertical +Flag
30 Main Vertical -Flag (GND)
31 Main OBS Rotor C
32 Main OBS Rotor H(GND)
33 Main OBS Stator D
34 Main OBS Stator E (2.5V Common OBS)
35 Main OBS Stator F 36 Main OBS Stator G (2.5V Common OBS)
37 Audio 1 HI (Alert audio)
38 Audio 1 LO (Alert audio)
39 LTG Bus HI
40 LTG Bus LO (GND)
41 GPS RS232 Out 3
42 GPS RS232 In 3
43 Main OBI Clock
44 Main OBI Data
45 Main OBI Sync
46 GPS Arinc-429 Out A
47 GPS Arinc-429 Out B
48 GPS Arinc-429 In 1 A
49 GPS Arinc-429 In 1 B
50 GPS Arinc-429 In 2 A
51 GPS Arinc-429 In 2 B
52 Audio 2 HI
53 Audio 2 LO
54 GPS RS232 Out 4
55 GPS RS232 In 4
56 GPS RS232 Out 1
57 GPS RS232 In 1
Signal Type Output Output Output Output Output Input Output Input Output Output Output Input Input Output Input Output Output Output Output Output Input Input Input Input Output Output Output Input Output Input
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Pin
Description
58 GPS RS232 Out 2
59 GPS RS232 In 2
60 Altitude Common (GND)
61 Altitude C4
62 Altitude C2
63 Altitude C1
64 Altitude B4
65 Altitude B2
66 Altitude B1
67 Altitude A4
68 Altitude A2
69 Altitude A1
70 Altitude D4 / Weight on Wheels Input (Helicopter use)
71 OBS Mode Select
72 Aircraft Power 2
73 CDI Source Select
74 COM Remote Recall Forward
75 COM Remote Recall Reverse
76 LTG BUS 2 HI
77 Aircraft GND
78 Aircraft GND
Table 38 P1001 Pin Description
6.1.2 P1002 Communication Connector
Note: This connector is not used in the IFD510/545/410.
Pins 1 2 3 4 5 6 7 8
Description Reserved Ethernet 1 TX+ Ethernet 1 TXCOM Microphone Key Intercom Microphone Audio HI COM Microphone Audio HI COM Audio HI Ethernet 1 RX+
9 Ethernet 1 RX-
Signal Type Output Input Input Input Input Input Input Input Input Input Input Input Input Input Input Input Input Input -
Signal Type -
Output Output Input Input Input Output Input Input
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Pins 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25
Description Synchro X Aircraft Power Aircraft Power Synchro Reference Signal + Transmit Interlock (Unused) COM Remote Transfer Reserved Intercom Microphone Audio LO COM Microphone Audio LO COM Audio LO Reserved Aircraft GND Aircraft GND Synchro Y Synchro Z Synchro Reference Signal -
Table 39 P1002 Pin Description
6.1.3 P1006 Navigation Connector
Note: This connector is not used in the IFD510/545/410.
Pins 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20
Description VOR/LOC +To VOR/LOC +From (VOR/LOC 2.5V Common) VOR/LOC +Flag VOR/LOC -Flag (VOR/LOC 2.5V Common) VOR/LOC +Left VOR/LOC +Right (VOR/LOC 2.5V Common) Com Monitor Audio HI VOR/LOC Composite Out VOR OBS Rotor C VOR OBS Rotor H (GND) VOR OBS Stator E/G (VOR/LOC 2.5V Common) VOR OBS Stator F VOR OBS Stator D Parallel DME - 8MHz VOR/LOC Superflag VOR/ILS Audio HI VOR/ILS Audio LO Serial DME - Clock Serial DME - Data Ser DME-Chan REQ/PAR DME - 4MHz
Signal Type Input Input Input Input Input Input Input Input Output Input Input Input
Signal Output Output Output Output Output Output Output Output Output
Output Input Input Output Output Output Output Output Output Input/output
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Pins 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44
Description Ser DME-RNAV Mode/PAR DME - 2MHz DME Common VOR/ILS Arinc-429 Out B VOR/ILS Arinc-429 Out A VOR OBI Clock VOR OBI Sync VOR OBI Data VLOC Remote Transfer ILS Energize Glideslope +Flag Glideslope +Down/-Flag (Glideslope 2.5V Common) Glideslope +Up Parallel DME - 1MHz Com Monitor Audio LO VOR/ILS Arinc-429 In B VOR/ILS Arinc-429 In A Parallel DME - 800KHz Glideslope Superflag Parallel DME - 400KHz Parallel DME - 200KHz Aircraft GND Parallel DME - 100KHz Parallel DME - 50KHz Aircraft Power
Table 40 P1006 Pin Description
6.1.4 P1050 Additional I/O Connector
Please note: This connector is not available on the IFD4XX.
Signal Input/output
Input Output Output Output Output Output Input Output Output Output Output Output Output Input Input Output Output Output Output
Output Output Input
Pins
Description
1 TAWS Inhibit IN
2 TAWS Audio Inhibit IN
3 Spare Input 4
4 Spare Input 3
5 Spare Input 2
6 Spare Input 1
7 Reserved
8 Reserved
9 Terrain Not Available Annunciate
10 Terrain Warning Annunciate
Signal Input Input Input Input Input Input
Output Output
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Pins 11 12 13 14 15 16
17-21 22-39
40 41 42 43 44-59 60 61 62 63 64 65-76 77 78
Description Terrain Caution Annunciate TAWS Inhibit Annunciate Spare Annunciate 2 Spare Annunciate 1 TAWS Audio Active Out Reserved Ground NO CONNECT ARINC 453 RX+ ARINC 453 RX GPS ARINC-429 Out 2A GPS ARINC-429 Out 2B NO CONNECT RS232 Out 5 RS232 IN 5 RS232 Out 6 RS232 IN 6 Ground NO CONNECT RS170 Video IN Ground
Table 41 P1050 Pin Description
6.1.5 Altitude Gray Code
Altitude Gray code input is connected on the following pins:
Description
Connector Pin
Altitude D4
P1001
70
Altitude A1
P1001
69
Altitude A2
P1001
68
Altitude A4
P1001
67
Altitude B1
P1001
66
Altitude B2
P1001
65
Altitude B4
P1001
64
Altitude C1
P1001
63
Altitude C2
P1001
62
Altitude C4
P1001
61
Altitude Common
P1001
60
Table 42 Altitude Gray Code Description
Signal Output Output Output Output Output
Input Input Output Output Output Input Output Input Input Input
Signal Type Input Input Input Input Input Input Input Input Input Input Input
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NOTE: Some transponders and altitude encoders do not have internal isolation diodes to prevent the unit from pulling the encoder lines to ground when the unit is off. These units will require the installation of a diode into harness for each encoder line.
6.1.6 Heading Input
Note: This section is N/A for the IFD510/545/410.
The IFD5XX/4XX can accept a 3-wire ARINC 407 Synchro heading input on the following connectors and pins:
Description
Connector Pin
Signal Type
Synchro X
Synchro Reference Signal + (26VAC 400 Hz)
Synchro Y
P1002
10
P1002
13
P1002
23
Input
Input Input
Synchro Z
P1002
24
Input
Synchro Reference Signal - (GND)
P1002
25
Input
Table 43 Synchro Heading Input
6.1.7 Main Course Deviation Indicator Output
The main indicator displays both lateral and vertical deviations, TO/From, and Flag indications from the NAV and GPS receivers.
6.1.7.1 Lateral/Vertical Deviations
The lateral and vertical deviations are on the following connector and pins:
Description Main +Left Main +Right Main +Up Main +Down
Connector Pin
P1001
21
P1001
22
P1001
27
P1001
28
Signal Type Output Output Output Output
Table 44 Main Course Deviation Output
6.1.7.2 TO/FROM Indication Flag
The To/From Flag indication flags are on the following connector and pins:
Description Main +To Main +From
Connector Pin
P1001
25
P1001
26
Table 45 Main TO/From Flag Output
Signal Type Output Output
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6.1.7.3 Navigation Flags The Navigation Flags is on the following connector and pins:
Description Main Lateral +Flag Main Lateral -Flag Main Vertical +Flag Main Vertical -Flag
Connector Pin
P1001
23
P1001
24
P1001
29
P1001
30
Table 46 Main Navigation Flag Output
Signal Type Output Output Output Output
6.1.7.4 Navigation Superflags The Navigation Superflags is on the following connector and pins:
Description Main Lateral Super Flag Main Vertical Super Flag
Connector Pin
P1001
17
P1001
18
Signal Type Output Output
Table 47 Main Navigation Superflag Output
Superflag outputs system voltage when valid and <.25 VDC when not valid. This output is capable of driving 500mA at 28 VDC or 250mA at 14 VDC.
6.1.7.5 OBS
The OBS is on the following connector and pins:
Description Main OBS Rotor C Main OBS Rotor (Ground) Main OBS Stator D Main OBS Stator E Main OBS Stator F Main OBS Stator G
Connector Pin
P1001
31
P1001
32
P1001
33
P1001
34
P1001
35
P1001
36
Table 48 Main OBS Output
Signal Type Output Output Input Output Input Output
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6.1.7.6 Annunciators Electrical Output
IFD5XX/4XX Installation Manual
Description VLOC Annunciate GPS Annunciate Waypoint Annunciate Terminal Annunciate Approach Annunciate Message Annunciate OBS Annunciate Integrity Annunciate LNAV GPS Select ILS/GPS Approach
Connector Pin
P1001
1
P1001
2
P1001
3
P1001
4
P1001
5
P1001
6
P1001
7
P1001
9
P1001
13
P1001
14
Signal Type Output Output Output Output Output Output Output Output Output Output
Table 49 Annunciator Output
All outputs sink up to 500 mA when activated. 6.1.7.7 Switch Inputs
Description OBS Mode Select CDI Source Select
Connector Pin
P1001
71
P1001
73
Signal Type Input Input
Table 50 Switch Inputs
The inputs are considered active if voltage to ground <1.9V or resistance to ground <375 . These inputs are considered inactive if voltage to ground is 11-33 VDC.
6.1.7.8 Time Mark Out
Description Time Mark Out
Connector Pin
P1001
16
Signal Type Output
Table 51 Time Mark Output
Outputs a 1ms ± 1µs wide pulse once every 1.0 Second ± 2 ms. Output sources 1 mA at >3.8 V and sinking 1 mA at less than 0.4 V.
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6.1.8 Serial Data
6.1.8.1 RS-232
Description RS-232 Output 1 RS-232 Input 1 RS-232 Output 2 RS-232 Input 2 RS-232 Output 3 RS-232 Input 3 RS-232 Output 4 RS-232 Input 4 RS-232 Output 5 RS-232 Input 5 RS-232 Output 6 RS-232 Input 6
Connector Pin
P1001
56
P1001
57
P1001
58
P1001
59
P1001
41
P1001
42
P1001
54
P1001
55
P1050
60
P1050
61
P1050
62
P1050
63
Table 52 RS-232 Input / Output
IFD5XX Only
6.1.9 ARINC 429
Signal Type Output Input Output Input Output Input Output Input Output Input Output Input
Description GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B GPS ARINC 429 IN 2 A GPS ARINC 429 IN 2 B VOR/ILS ARINC 429 OUT A * VOR/ILS ARINC 429 OUT B * VOR/ILS ARINC 429 IN A * VOR/ILS ARINC 429 IN B * GPS ARINC 429 OUT A GPS ARINC 429 OUT B
Connector Pin
P1001
46
P1001
47
P1001
48
P1001
49
P1001
50
P1001
51
P1006
24
P1006
23
P1006
36
P1006
35
P1050
42
P1050
43
Signal Type Output Output Input Input Input Input Output Output Input Input Output Output
Table 53 ARINC 429 Input / Output
IFD5XX only, * N/A for IFD510/545/410
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6.1.10 ARINC 453
Description ARINC 453 RX + ARINC 453 RX -
IFD5XX/4XX Installation Manual
Connector Pin
P1050
40
P1050
41
Table 54 ARINC 453 Input
Signal Type Input Input
6.1.11 RS170 Video
Description RS170 Video In High RS170 Video In Low
Connector Pin
P1050
77
P1050
78
Table 55 RS170 Video Input
Signal Type Input Input
6.1.12 Com/VOR/ILS Audio Electrical Characteristics
Note: This section is N/A for IFD510/545/410. 6.1.12.1 Com Microphone Key
Description COM MIC Key
Connector Pin
P1002
4
Signal Type Input
Table 56 VHF Communication Microphone Key
This input is active if either the voltage to ground <1.9V or the resistance to ground is <375. This input is considered inactive if the voltage to ground is 11-33 VDC.
Activating the COM MIC Key will cause the transmitter to transmit the audio on the COM MIC Audio HI.
6.1.12.2 Com Microphone Audio, INTERCOM Microphone Audio
Description COM MIC Audio HI COM MIC Audio LO INTERCOM MIC HI INTERCOM MIC LO
Connector Pin
P1002
6
P1002
18
P1002
5
P1002
17
Table 57 VHF Communication Audio
520 input impedance, supply 9V via 620.
Signal Type Input Input Input Input
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6.1.12.3 Com Audio, VOR/ILS Audio
Description Com Audio HI Com Audio LO VOR/ILS Audio HI VOR/ILS Audio LO
Connector Pin
P1002
7
P1002
19
P1006
16
P1006
17
Signal Type Output Output Output Output
Table 58 VHF Communication and Navigation Audio Output
Each supply 65mW into 150 . They are balanced outputs and LO output must be connected.
6.1.12.4 Discrete Inputs
Description Transmit Interlock (Unused) Com Remote Transfer VLOC Remote Transfer Com Remote Recall, Forward Com Remote Recall, Reverse
Connector Pin
P1002
14
P1002
15
P1006
28
P1001
74
P1001
75
Signal Type Input Input Input Input Input
Table 59 VHF Communication and Navigation Switch Inputs
This input is active if either the voltage to ground <1.9V or the resistance to ground is <375. This input is considered inactive if the voltage to ground is 11-33 VDC.
COM Remote Transfer and VLOC Remote Transfer are momentary inputs. Momentarily depressing the VLOC or Com Remote transfer button toggles the active and #1 standby frequencies. Momentarily depressing the COM Remote Recall button inserts the next frequency in the Com preset list into the #1 standby slot.
6.1.12.5 Standby Com Monitor
Description Com Monitor Audio HI Com Monitor Audio LO
Connector Pin
P1006
7
P1006
34
Table 60 Standby Communication Output
Signal Type Output Output
This optional signal use can be used with audio panels that have a means of selecting the #1 standby com audio (e.g. Avidyne AMX240).
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6.1.13 VOR/ILS Indicator Electrical Characteristics
Note: This section is N/A for IFD510/545/410. 6.1.13.1 Superflag
Description VOR/LOC Superflag Glideslope Superflag
Connector Pin
P1006
15
P1006
38
Signal Type Output Output
Table 61 Navigation Superflag Output
The output supplies not less than 500 mA on a 28 volt system and 250 mA on a 14 volt system with the output voltage at (Aircraft voltage 3VDC) when the flag is to be out of view. The output voltage with respect to ground is less than 3 VDC when the flag is to be in view.
6.1.13.2 RMI/OBI Electrical Characteristics
Description Main OBI Clock Main OBI Sync Main OBI Data
Connector Pin
P1001
43
P1001
45
P1001
44
Table 62 P1001 OBI Output
Signal Type Output Output Output
Description VOR OBI Clock VOR OBI Sync VOR OBI Data
Connector Pin
P1006
25
P1006
26
P1006
27
Table 63 P1006 OBI Output
Signal Type Output Output Output
The output is active low.
6.1.14 DME Tuning
Note: This section is N/A for IFD510/545/410.
The IFD5XX/4XX can channel a DME based on the tuned VLOC frequency. The IFD5XX/4XX can be connected to a DME via 2x5, BCD, Slip parallel, or King Serial DME channeling format.
6.1.14.1 Serial/Parallel Tuning
Description
NAV PAR DME 8MHz SER DME CHAN REQ/PAR DME 4MHz
Connector Pin
P1006
14
P1006
20
Signal Type Output
Output*
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SER DME RNAV MODE/PAR DME 2MHz
P1006
21
Output*
NAV PAR DME 1MHz
P1006
33
Output
NAV PAR DME 800 kHz
P1006
37
Output
NAV PAR DME 400 kHz
P1006
39
Output
NAV PAR DME 200 kHz
P1006
40
Output
NAV PAR DME 100 kHz
P1006
42
Output
NAV PAR DME 50 kHz
P1006
43
Output
NAV DME COMMON
P1006
22
Input
Table 64 DME Serial/Parallel Output
* Used for 2x5 parallel DME tuning.
NAV DME Common must be pulled low for the IFD5XX/4XX to channel the DME. DME is active if the voltage to ground is <1.9 V or the resistance to ground is <375 .
Outputs is not more than 1.0V while sinking 20 mA.
6.1.14.2 King Serial DME Tuning
Description
Connector Pin
NAV Serial DME DATA
P1006
19
NAV Serial DME Clock
P1006
18
Serial DME CHAN REQ/PAR DME 4MHz
P1006
20
Serial DME RNAV Mode/PAR DME
P1006
21
2MHz
NAV DME Common
P1006
22
Signal Type Output Output*
Output*
Output Output
Table 65 DME Serial Tuning
Output high is >8V when driving a 360 and < 10mV for a low.
NAV DME Common must be pulled low for the IFD5XX/4XX to channel the DME. DME is active if the voltage to ground is <1.9 V or the resistance to ground is <375 .
6.2 Bezel Lighting
The IFD5XX/4XX can be connected to any of the following avionics lighting sources: 5/14/28VDC or 5 VAC. Dimming controls are described in Section 7.5.6.
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6.3 Traffic System
The IFD5XX/4XX can be connected to Traffic Systems either by RS232 or ARINC 429. The IFD5XX/4XX supports the following Traffic Systems:
Manufacturer
Model
Data Format
Notes
Avidyne Corporation
TSA6XX, TAS6XXA, 9900BX
RS232 or ARINC
429
RS-232 preferred
Avidyne Corporation
Skytrax100 (formerly MLB100)
(Navworx 2000011-()-())
RS232 or ARINC
429
RS-232 preferred
Avidyne Corporation
Skytrax100B
RS232 or ARINC
429
RS-232 preferred
L3 Communications
SKY497, SKY899
ARINC 429
Bendix/King
KTA-870, KMH880
ARINC 429
Garmin
GTS800/820/850
ARINC 429
Table 66 Traffic Systems
6.4 Lightning Detection System
The IFD5XX/4XX can be connected to Lightning Detection Systems via RS232. The IFD5XX/4XX supports the following Lightning Detection Systems:
Manufacturer
Model
Data Format
Notes
Avidyne Corporation
TWX670
RS232
"Native" format
L3 Communications
WX500
RS232
WX500 must set both the 232 Input and 232 Output
on the IFD5XX/4XX.
Table 67 Lightning Detection System
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IFD5XX/4XX Installation Manual 6.5 Datalink Weather
The IFD5XX/4XX can be connected to Datalink Weather Systems via RS232. The IFD5XX/4XX supports the following Datalink Weather Systems:
Manufacturer Avidyne Corporation
Freeflight Systems Heads-up Technologies
Garmin
Garmin WSI
Model MLB700
Data Format
RS232
Notes
SkyTrax100(formerly MLB100) [Navworx 200-0011-()-()] Skytrax 100B
FDL-978-RX
XMD-076
GDL69/69A P/N 011-00986-00 or 011-00987-00
only Pre Software 10.2.3.1 With Software 10.2.3.1 or later P/N 011-
03177-X0 will also work GDL 88 AV300 AV350
Table 68 Weather Datalink
RS232 RS232 RS232 RS232 RS232
RS232 RS232
IFD with s/w 10.1.0 or later
IFD with s/w 10.1.0 or later
IFD with s/w 10.1.0 or later
IFD with s/w 10.2.3.1 or later
Garmin Software version 4.01 or later For first generation
GDL's
6.6 Audio Panels
The IFD5XX/4XX can be connected to various Audio Panels via analog connections. The IFD5XX/4XX supports the following Audio Panels:
Manufacturer Avidyne Garmin
Honeywell (Bendix/King) PS Engineering
Model
AMX240
SL10/ SL10MS/ SL10M/ SL10S/ SL15/ SL15M/
GMA340/ GMA347
KMA24/ KMA24H-70/71 KMA26/ KMA28
PMA6000/ PMA 7000 Series/ PMA 8000 Series
Data Format Analog Audio Analog Audio
Analog Audio Analog Audio
Notes
Table 69 Audio Panels
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6.7 GAD 42
The IFD5XX/4XX can be connected to the Garmin GAD42 Interface Adapter.
If the IFD5XX/4XX is replacing a GNS530/W or GNS430/W that had previously been connected to a GAD42, then no action is required since the configuration is already saved in the GAD42.
If this is a new installation of an IFD5XX/4XX (i.e. not replacing an existing GNS-530/W or GNS-430/W) or if the GAD42 had to be replaced for service, then the GAD42 must be configured via a manual strapping method as described in Garmin P/N 190-00159-00 GAD42 Installation Manual, Section 5.1.
6.8 Air Data System Sources
The IFD5XX/4XX can be connected to either Uncorrected or Baro-corrected Altitude Sources. The IFD5XX/4XX can be connected to the following Air Data Systems:
Manufacturer Aspen Avidyne Garmin B & D Honeywell (Bendix/King) Insight
Model EFD1000 Entegra PFD G500/600 90004-003 KDC281/481 TAS 1000
Data Format ARINC 429 ARINC 429 ARINC 429 ARINC 429 ARINC 429
RS232
Notes Low Speed Low Speed Low Speed Low Speed Low Speed
Table 70 Air Data Systems
6.8.1.1 Uncorrected Pressure Altitude Sources
The IFD5XX/4XX can accept uncorrected altitude from multiple sources in the following formats: ARINC 429, RS232, or a Gray Code altitude encoder. If multiple altitude sources are connected, the IFD5XX/4XX will use the altitude sources in this order (highest first):
1. ARINC 429 ADC 2. ARINC 429 EFIS 3. ARINC 429 Traffic Advisory System 4. RS232 FADC 5. RS-232 Altitude Encoder 6. Parallel Altitude Encoder (Gray Code)
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6.8.1.2 Baro-corrected Altitude Sources
The IFD5XX/4XX can accept baro-corrected altitude from multiple sources. The IFD5XX/4XX can accept Altitude information from altitude Air Data Systems in the following formats: ARINC 429 or RS232. If multiple altitude sources are connected to the IFD5XX/4XX, the IFD5XX/4XX will use the altitude sources in this order (highest first):
1. ARINC 429 INS/IRU 2. ARINC 429 EFIS 3. ARINC from Transponder 4. RS232 FADC
6.8.1.3 Other Air Data Sources
The IFD5XX/4XX can be connected to Air Data Systems that transmit the following labels via ARINC 429 if all the following is true:
· The Air Data Computer provides the following labels: 203 Pressure Altitude 204 - Barometric- Corrected Altitude 210 True Airspeed 211 Total Air Temperature 213 Static Air Temperature
· The Air Data source is TSO approved and has a separate installation approval · All wiring must be installed per the Air Data Computer's installation data
6.9 Heading System Sources
The IFD5XX/4XX can accept Heading data from multiple sources. The IFD5XX/4XX can accept heading information from Heading Systems in the following formats: ARINC 429 or RS232. If multiple heading sources are connected to the IFD5XX/4XX, the IFD5XX/4XX will use the heading sources in this order (highest first):
1. ARINC 429 INS/IRU 2. ARINC 429 EFIS 3. ARINC 429 from GAD42 4. ARINC 429 from EHSI 5. ARINC 429 from GTX 33/330 6. ARINC 429 Traffic Advisory System 7. Synchro Heading (N/A for IFD510/545/410) 8. RS232 FADC 9. RS232 Lightning Detection System (The WX500 can only be used as a heading source
if it is configured for a Synchro output.) The IFD5XX can be connected to the following IRU/AHRS systems:
Manufacturer Collins
Model AHS-85E
Data Format
Notes
ARINC 429 High Speed
Table 71 IRU/AHRS Systems
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The Avidyne IFD5XX/4XX can accept heading information via ARINC 429 from other IRU/AHRS sources if the following labels are provided:
· 314 - True Heading · 320 - Magnetic Heading IRU/AHRS not listed in the table above can still be approved if the following conditions are met: · The IRU/AHRS provides ARINC 429 labels 314 and/or 320; · The IRU/AHRS installation is previously FAA approved; · The IFD5XX/4XX must be installed per Section 4.5.1. · The IFD5XX/4XX must pass the ground test in Section 7.6.16 before returning aircraft
to service
6.10 Multifunction Displays
The IFD5XX/4XX can be connected to Multifunction Display Systems via RS232 or ARINC 429. The IFD5XX/4XX supports the following Multifunction Display Systems:
Manufacturer
Model
Data Format
Notes
Garmin
MX20
RS232
· Aviation No Alt format for MX20 version 5.5 and earlier
· Aviation format for MX20 version 5.6 and later.
Garmin
GMX200
RS232
Avidyne Corporation
EX500/EX600/EX5000
ARINC 429
· Aviation format for all GMX200 versions
· Use GAMA format 2, low speed
· MFD software P/N 53000193-( ) or later is required
Avidyne Corporation
FlightMax FSD Series
RS232
· GAMA output may also be used. However, flight plans with an Arc will be displayed as a gap.
Table 72 Multifunction Display
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6.11 Forward Looking Terrain Alerting
This section will describe the external interfaces for the FLTA interface. Note: The IFD5XX/4XX does not contain TSO-C151()-compliant TAWS functionality and may not be used to satisfy the 14 CFR 91.223 TAWS requirement on those airplanes where it applies. FLTA does provide aural alerting to the pilot of projected terrain (ground and obstacle) conflicts. FLTA also has the ability to command the various TAWS remote annunciators to light up as appropriate. Section 7.5.4 has instructions for turning FLTA on or off.
6.11.1 Audio
Pin Name Audio 1 HI Audio 1 LO Audio 2 HI Audio 2 LO
Connector P1001 P1001 P1001 P1001
Pin
I/O
37
Output
38
Output
52
Output
53
Output
Table 73 Terrain Awareness Audio Output
The audio output 1 is a low impedance output. 100mW at 500-ohm. The audio output 2 has an output impedance of 240-ohm and is capable of driving 100mW into a 500-ohm load.
6.11.2 Annunciators
Pin Name Terrain not available annunciate Terrain Warning Annunciate
Terrain Caution Annunciate
TAWS Inhibit Annunciate
Connector P1050
P1050 P1050 P1050
Pin
I/O
9
Output
10
Output
11
Output
12
Output
Table 74 Terrain Awareness Annunciator Output
6.12 TAWS/EGPWS Output
The IFD does not accept any data for use or display from any TAWS or EGPWS system. The IFD5XX/4XX is capable of sending position data to the following EGPWS systems:
Manufacturer Honeywell
Model KGP560
Notes
Serial GPS position output to the KGP560 only
Table 75 TAWS/EGPWS Output
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6.13 ADS-B Transponder/UAT Output
The IFD5XX/4XX will transmit ADS-B GPS position data to the following compatible ADS-B capable transponders/UAT. The ADS-B out transmitters listed in the Table below have been tested with Avidyne IFD4XX/IFD5XX GPS receivers (GPS position source(s)) and have been found to be compliant combinations to meet all ADS-B out requirements compliant with 14 CFR 91.217.
Manufacturer Avidyne
Model AXP340
Avidyne
AXP322
Notes
· ADS-B output requires a separate installation approval. See Avidyne AXP322/AXP340 AML STC SA00352BO.
· For ADS-B out compliance, a squat switch is required for automatically selecting the transponder air or ground mode of operation. For aircraft without a squat switch, connect the squat switch input of the transponder to P1001 pin 8 of one of the IFD5XX/4XX. Set the transponder to accept an active low when performing that squat switch setup.
· The IFD5XX/4XX retransmits the Altitude data received from external altitude devices to AXP340. This is a non-TSO function of the IFD5XX/4XX and must be tested and approved by the installer prior to returning the aircraft to service. The IFD5XX/4XX will use the airdata source with the highest priority, reference Section 6.8.1.1. Installers must ensure the airdata source being used for transponder Mode C transmissions complies with 14 CFR 91.217. After installation, the transponder system must be tested per 14 CFR 91.411 to verify the airdata retransmitted by IFD5XX/4XX is operating correctly prior to return to service.
The Hardware and Software Design Assurance for the Altitude Retransmission is Level B and C respectively.
The IFD5XX/4XX has a maximum internal latency of 340 mS for retransmission the altitude data.
· See Figure D - 44 for AXP340 interconnect.
· ADS-B output requires a separate installation approval. See Avidyne AXP322/AXP340 AML STC SA00352BO.
· For ADS-B out compliance, a squat switch is required for automatically selecting the transponder air or ground mode of operation. For aircraft without a squat switch, connect the squat switch input of the transponder to P1001 pin 8 of one of the IFD5XX/4XX. In either case, set the transponder to "Avidyne" when performing the squat switch setup. See section 7.5.13
· The IFD5XX/4XX retransmits the Altitude data
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GTX330ES
IFD5XX/4XX Installation Manual
received from external altitude devices to AXP322. This is a non-TSO function of the IFD5XX/4XX and must be tested and approved by the installer prior to returning the aircraft to service. The IFD5XX/4XX will use the airdata source with the highest priority, reference Section 6.8.1.1. Installers must ensure the airdata source being used for transponder Mode C transmissions complies with 14 CFR 91.217. After installation, the transponder system must be tested per 14 CFR 91.411 to verify the airdata retransmitted by IFD5XX/4XX is operating correctly prior to return to service.
The Hardware and Software Design Assurance for the Altitude Retransmission is Level B and C respectively.
The IFD5XX/4XX has a maximum internal latency of 340 mS for retransmission the altitude data.
· See Figure D - 44 for AXP322 interconnect.
· IFD5XX/4XX must have software 10.1.0 or later
· The IFD4XX/IFD5XX AML STC SA00343BO approves ADS-B out capability for this ADS-B OUT transmitter and GNSS position sensor combination to comply with 91.227.
· For ADS-B out compliance, a squat switch is required for automatically selecting the transponder air or ground mode of operation. For aircraft without a squat switch, connect the squat switch input of the transponder to P1001 pin 8 of one of the IFD5XX/4XX. Set the transponder to accept an active low when performing that squat switch setup.
· The IFD5XX/4XX retransmits the Altitude data received from external altitude devices to GTX330ES. This is a non-TSO function of the IFD5XX/4XX and must be tested and approved by the installer prior to returning the aircraft to service. The IFD5XX/4XX will use the airdata source with the highest priority, reference Section 6.8.1.1. Installers must ensure the airdata source being used for transponder Mode C transmissions complies with 14 CFR 91.217. After installation, the transponder system must be tested per 14 CFR 91.411 to verify the airdata retransmitted by IFD5XX/4XX is operating correctly prior to return to service.
The Hardware and Software Design Assurance for the Altitude Retransmission is Level B and C respectively.
The IFD5XX/4XX has a maximum internal latency of 340 mS for retransmission the altitude data.
· See Figure D - 50 for GTX330ES interconnect.
· IFD5XX/4XX must have software 10.2 or later
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GTX335 GTX345
NGT9000R NGT9000R+ NGT9000RD NGT9000RD+
· The IFD4XX/IFD5XX AML STC SA00343BO approves ADS-B out capability for this ADS-B OUT transmitter and GNSS position sensor combination to comply with 91.227.
· For ADS-B out compliance, a squat switch is required for automatically selecting the transponder air or ground mode of operation. For aircraft without a squat switch, connect the squat switch input of the transponder to P1001 pin 8 of one of the IFD5XX/4XX. Set the transponder to accept an active low when performing that squat switch setup.
· The IFD5XX/4XX retransmits the Altitude data received from external altitude devices to GTX3X5. This is a non-TSO function of the IFD5XX/4XX and must be tested and approved by the installer prior to returning the aircraft to service. The IFD5XX/4XX will use the airdata source with the highest priority, reference Section 6.8.1.1. Installers must ensure the airdata source being used for transponder Mode C transmissions complies with 14 CFR 91.217. After installation, the transponder system must be tested per 14 CFR 91.411 to verify the airdata retransmitted by IFD5XX/4XX is operating correctly prior to return to service.
The Hardware and Software Design Assurance for the Altitude Retransmission is Level B and C respectively.
The IFD5XX/4XX has a maximum internal latency of 340 mS for retransmission the altitude data.
· See Figure D - 48 and Figure D - 49 for GTX3X5 interconnect.
· IFD5XX/4XX must have software 10.2 or later
· ADS-B output requires a separate installation approval. This system utilizes an internal position source for ADS-B out compliance. See L3 STC.
· For ADS-B out compliance, a squat switch is required for automatically selecting the transponder air or ground mode of operation. For aircraft without a squat switch, connect the squat switch input of the transponder to P1001 pin 8 of the controlling IFD5XX/4XX for IFD's with software 10.0.0 or higher. Set the transponder to accept an active low on ground when performing that squat switch setup.
· The NGT9000XX needs a pressure altitude input
· The NGT9000XX has its own internal GPS receiver
· IFD5XX/4XX must have software 10.2.3.1 or later for the control logic
Table 76 ADS-B Output
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6.14 Autopilot
The IFD5XX/4XX can be connected to various Autopilot Systems via analog or ARINC 429 connections. The IFD5XX/4XX supports the following Autopilot Systems:
Manufacturer
Model
Data Format
Notes
Avidyne
DFC90
Serial
Avidyne and Aspen PFDs
KAP100/140/150, KFC150/200/250/275 /300/325
Analog Deviation, Discrete
KCP 320
Honeywell (Bendix/King)
KFC225
Analog Deviation, Discrete, ARINC
429 GPSS
Dual IFD installations require only the IFD
connected to the autopilot be setup for Prompt (See section
7.5.4)
KFC400
ARINC 429
Century
I/II/III/IV, 21/31/41, 2000, Trident
AK 1081
Analog Deviation, Discrete
ARINC 429 GPSS
S-TEC (Cobham)
System 20/30/40/50/ 55/61/62/GPSS/65 System 55X
ST-901
Analog Deviation, Discrete
Analog Deviation, Discrete, ARINC
429 GPSS
ARINC 429 GPSS
Collins
APS 65 ( ) APS 3000
Analog Deviation, Discrete
ARINC 429
Requires Software 10.2.2 or higher
Table 77 Autopilot Systems
6.15 Video Input
The IFD5XX can be connected to the following RS-170 video sources:
Manufacturer Various
Model FAA Approved
Data Format RS-170
Notes
Table 78 Video Systems
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6.16 Radar Display and Control
The IFD5XX/4XX can be connected to the following radar system:
Manufacturer
Model
Data Format
Notes
Honeywell (Bendix/King)
RDR2000
ARINC 429 (out) ARINC 453 (in)
Only the IFD5XX can control and display radar. The IFD4XX can display radar via crossfill if a IFD5XX is the primary connection
Table 79 Radar Systems
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7. Configuration and Checkout
After completing installation, a complete installation checkout should be performed. Complete the following sections to verify the installation is installed correctly. Prior to configuring the IFD5XX/4XX unit, the following checks should be performed.
7.1 Wiring Check
Verify wiring is properly installed and secured. Verify the wiring does not interfere with the flight controls. Verify all wiring connected to IFD5XX/4XX is connected correctly to the unit. Caution: Failure to properly connect aircraft wiring to the IFD5XX/4XX may result in damage to the IFD5XX/4XX or to the equipment connected to the IFD5XX/4XX.
7.2 Mounting Check
Verify the IFD5XX/4XX tray is securely installed to the airframe.
7.3 Chassis ID Setting
For dual IFD5XX/4XX installations, it is imperative that the proper Chassis ID settings are established for each IFD via dip switches located along the right side of the IFD5XX/4XX outer chassis. Not doing so will result in multiple error messages and degraded performance when two or more IFDs are installed in an airplane.
Figure 10 IFD5XX/4XX DIP Switches
At installation time, determine which IFD is to be designated as IFD #1 and which is to be designated as IFD #2 (Note, there is no operational difference, This is a Databus address assignment necessity). Set the side chassis ID dip switches per the table below:
IFD Position Designation IFD #1 IFD #2
DIP switch selections (up, up, up)
(down, up, up)
Table 80 DIP Switch Configuration
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7.4 Unit Installation
Install unit in the tray using the captive 3/32" Hex screw. Verify the connectors are fully engaged prior to powering on the unit.
7.5 Configuration
The IFD5XX/4XX can be configured in the aircraft. This section will describe the procedures for configuring the IFD5XX/4XX. Configuration consists of setting up communication protocols in Maintenance Mode, designating specific types of equipment to be integrated and setting up system settings. Configuration also consists of setting up User Options preferences in non-Maintenance Mode via the SYS tab of the AUX page. For new installations, use this section to configure the IFD5XX/4XX for the specific airplane. For replacement installations in which the IFD5XX/4XX is replacing a GNS 530/W or GNS 430/W, use Appendix F: Configuration Setup of this manual to first record the configuration of the GNS530/W or GNS430/W that is being replaced by the IFD5XX/4XX and then using that recorded data, use the IFD5XX/4XX Maintenance Mode pages as defined in this section and Appendix F: Configuration Setup to properly set up and record configurations.
7.5.1 Maintenance Mode
The Maintenance Mode can be accessed by using the following procedures (on the ground only):
1. Power on the IFD5XX/4XX 2. Acknowledge all start up screens by pressing "Enter" 3. Press Proceed Line Select Key (LSK) followed by the Confirm LSK on the database
acknowledgement screen (if shown) 4. Select the "AUX" function key to display the Auxiliary Page. Press on the right side
of the "AUX" Function key until the "SYS" tab is shown 5. Select "Status/Software" LSK by pressing associated button until "Update
Databases" appears. (If shown) 6. Select "Update Databases" LSK by pressing the associated button. Press the
"Confirm" LSK after it appears. The screen will blank for several seconds before coming up in Maintenance Mode
Please note: Screen Page numbers shown below may not match unit.
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7.5.2 ARINC 429 Port Configuration (Page 1)
The ARINC 429 can be selected individually for each ARINC 429 Transmit and Receive Port. Each Transmit and Receive Port will have a "Speed" selection and "Data" selection.
Figure 11 IFD5XX ARINC 429 Configuration Page
Note: Shown is the IFD4XX ARINC 429 Config Page. The IFD5XX Config Page has an OUT 1 and OUT 2. OUT 2 on the IFD5XX has only 3 settings, OFF, ARINC 743A, and Onboard Radar
The "Speed" Selection will have the following options:
Selection Low High
Description Standard low-speed ARINC 429 (nominally 12.5 Kb per second)
High-speed ARINC 429 (nominally 100Kb per second)
Table 81 ARINC 429 Speed Selection
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The "Data" will have the following INPUT options:
Selection
Description
Off
No device connected to this ARINC 429 input
Airdata
Altitude, temperature, and speed information from the following Air Data Systems:
B&D 2600, 2601, 2800, 90004-003, Bendix/King KAD 280/480, Shadin ADC 2000
Airdata/AHRS Heading, altitude, temperature, and speed information from an Air Data/AHRS system.
EFIS
Selected course, heading, and joystick waypoint information from a EFIS system.
Certain versions of the Collins and Honeywell EFIS may be compatible with this format.
EFIS/Airdata
Selected course, heading, joystick waypoint, altitude, temperature, and speed information.
Flight Control
Selected course information from the following Flight Control systems:
Bendix/King KFC400
Garmin GAD 42 Selected course, heading, and true airspeed data from Garmin GAD 42.
Garmin GDL 88 Traffic
Garmin GDL 88 Traffic from the GDL 88/GTX 345 This ARINC 429 speed should be set to the high speed.
Garmin GDL 88 Traffic W/TCAS
Garmin GDL 88 Traffic W/TCAD
Garmin GDU
Garmin GDL 88 with a Garmin GTS 800/820/825 or a L-3 SKY497/SKY 899 System Unsupported, reserved for future use This ARINC 429 speed should be set to the high speed.
Garmin GDL 88 with a Avidyne TAS6XX or Ryan 9900BX System Unsupported, reserved for future use This ARINC 429 speed should be set to the high speed.
Selected course, heading, altitude, temperature and speed information from the following systems:
Garmin GDU (G500/G600)
Garmin GTX 330 Garmin GTX330 (No TIS)
This ARINC 429 speed should be set to the high speed.
Garmin GTX 330 Garmin GTX 330 w/TIS
w/Traffic
This ARINC 429 speed should be set to the high speed.
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Honeywell EFIS INS/IRU
RADAR Graphics
Selected course, heading, and joystick waypoint information from the following EFIS systems:
Aspen EFD1000 (If connected to an ACU1, set the ARINC 429 speed to low speed. If connected to an ACU2 and using ADF, RADALT or Remote OAT data set the ARINC 429 speed to high speed, otherwise low speed.) Honeywell Primus 1000 Avidyne EXP5000*
Heading information from the following Inertial systems: Bendix/King KAH 460 Collins AHC 85 Honeywell Laseref Litef LTR 81 Litton LTN 90-100, LTN 91, LTN 92
Joystick waypoint information from a RADAR graphics unit
Sandel EHSI
Selected course and heading information from the following EHSI systems: Sandel SN 3308 Sandel SN 3500 Avidyne EXP5000*
Traffic Advisory
Traffic information from the following traffic advisory systems: Bendix/King KTA-870, KMH880 Garmin GTS 800/820/850 Garmin GDL 88 Avidyne TAS6XX (but RS-232 is preferred) Ryan 9900BX (but RS-232 is preferred) L3 Communications SKY497 SkyWatch L3 Communications SKY899 SkyWatch HP
MLB 100 Traffic Avidyne SkyTrax100/MLB100 or Freeflight FDL-978-RX Traffic (But RS232 is preferred)
Table 82 ARINC 429 Input Selection
*Honeywell EFIS selection is preferred as it has more label information
Note: Only ARINC 429 Traffic is shared between IFDs on the CrossSync line, all other ARINC 429 devices should be wired to both IFDs in dual IFD installations since ARINC 429 data is not shared between IFDs on the CrossSync line.
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The "Data" will have the following OUTPUT options:
Selection
Description
Off
No device(s) connected to ARINC 429 output
ARINC 429
Standard ARINC 429 output (non-GAMA)
GAMA 429
ARINC data as define by the General Aviation Manufacturers' Association (GAMA) General Aviation Subset, 2nd Edition. The output data includes navigation, flight plan information to the following systems:
Garmin GAD 42 Interface Adapter
Collins EFIS 84 (select "Non-WAAS" on the IFD)
Bendix/King EFS 40/50 with update SW15/01 (GPS vertical guidance provided on EFIS)
Certain other versions of Collins EFIS may also be compatible with this format.
GAMA 429 Bendix/King
ARINC 429 data as defined by the GAMA General Aviation Subset, 2nd Edition. The output data includes navigation, flight plan and GPS vertical guidance information to the following systems:
Bendix/King EFS 40/50 without SW15/01 update (GPS vertical guidance provided on EFIS)
GAMA 429 Graphics
ARINC 429 data as defined by the GAMA General Aviation Subset, 2nd Edition including GAMA Graphics Protocol `A'. This format outputs intersection symbols as generic waypoint symbols. The output data includes navigation and flight plan information (including graphical representation of the flight plan procedures) to the following systems:
Honeywell Primus 1000
GAMA 429 Graphics w/ INT
ARINC 429 data as defined by the GAMA General Aviation Subset, 2nd Edition including GAMA Graphics Protocol `A'. The output data includes navigation and flight plan information (including graphical representations of flight plan procedures) to the following systems:
Sandel SN3308
Sandel SN3500
Aspen EFD1000 (see note below)
Avidyne EX500
Avidyne EX600
Avidyne EX5000
Note: When integrating an Aspen EFD1000 with a dual IFD5XX/4XX installation, ensure the "CRS SDI" field in the Aspen setup pages (page 18) is set to Nav 1/2 and not Common.
GAMA 429 Pro ARINC 429 data as defined by the GAMA General Aviation Subset,
Line 21
2nd Edition.
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Selection
Description
GAMA 429 Sextant
GAMA 429 Nonstandard
ARINC 743A
Onboard Radar
ARINC 429 data as defined by the GAMA General Aviation Subset, 2nd Edition
ARINC 429 data that is not necessarily conforming to the GAMA General Aviation Subset, 2nd Edition.
ARINC 429 - 743A labels
Honeywell RDR2000
Table 83 ARINC 429 Output Selection
SDI
Note: It is important in dual IFD installations that the corresponding SDI selection be made properly. That typically means selecting LNAV 1 or LNAV 2.
Selection
Description
Common
Rx: Accepts all 429 inputs
Tx: Generates all 429 outputs with SDI = 0
LNAV 1
Number 1 (Pilot) long-range navigator
RX: Accepts 429 inputs with SDI = 0 or 1.
TX: Generates all 429 outputs with SDI = 1.
LNAV 2
Number 2 (Copilot) long-range navigator
RX: Accepts 429 inputs with SDI = 0 or 2.
TX: Generates all 429 outputs with SDI = 2.
Table 84 SDI Selection
VNAV Selection
Disable Labels
Enable Labels
Description
ARINC 429 labels associated with GPS-based vertical guidance (labels 117G and 327G) are not transmitted in the output data stream.
Note: If replacing an existing GNS-530 and the VNAV field was not present on the 530, then select "Disable" on the IFD5XX/4XX.
ARINC 429 labels associated with GPS-based vertical guidance (labels 117G and 327G) are transmitted in the output data stream. ARINC 429 vertical:
Sandel SN3500
Aspen EFD1000
Other systems may also use these labels.
Table 85 VNAV Selection
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7.5.3 RS-232 Port Configuration (Page 2)
The RS-232 Configuration Page allows the configuration Inputs and Outputs to match that of the equipment installed in the aircraft.
Figure 12 RS-232 IFD5XX Configuration Page
Note: Shown is an IFD5XX Main RS232 Config Page. The IFD4XX only has 4 inputs and outputs
Note: For s/w 10.2.0 and earlier, if you configure Skytrax WX, Capstone Wx, MLB Wx, or WX500 on any input channel, the same numbered output channel cannot be configured with any of the following; ADS-B (Avi), ADSB, ADS-B+ (G), GDL 88, Aviation, Avtn no alt, HW EGWS, MapMX.
The following selections can be made on the RS-232 Input.
Channel Inputs
Selection
Description
Off Arnav/ei-fuel
AXP322 CrossSync
No device(s) connected to input of this channel Serial fuel flow information from the following units: ARNAV FC-10, FT-10 Electronics International FP-5L Select for Avidyne AXP322 Remote Transponder Serial transfer of flights plans and user waypoints and cross-side data (e.g. RS-232 Datalink, traffic, lightning, etc) between IFD5XX/4XX units. (Transponder and VHF control are not cross synced)
Note: This is only an option for CHNL 3.
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Selection GDL 691
MLB7001 XMD0761 XMD076 AUX1
Skytrax Wx1 SkyTrax Trfc2 SkyTrax Trfc+Wx1,2 Capstone Wx1 Capstone Trfc2 Capstone Trfc+Wx1,2 Capstone HS Wx1 Capstone HS Trfc2 Capstone HS
Trfc+Wx1,2 MLB100 Wx1 Freeflight1,2
NGT9000R Icarus-alt
Ryan TCAD2 Shadin-adc
Description
Serial data input for in-flight access to weather and messaging from the following units: Garmin GDL69/69A P/N 011-00986-00 or 011-00987-00 only (Garmin software version 4.01 or later) pre Avidyne software 10.2.3.1. With software 10.2.3.1 and later P/N 011- 03177-X0 will also work
Serial weather data information from the Avidyne MLB700
Serial weather data information from the Heads-up XMD-076 Read-only serial weather data information from the Heads-up XMD076 to be used when a different device is controlling the Heads-up device.
Serial weather data only information from the Avidyne Skytrax100/MLB100 or Freeflight FDL-978-RX
Serial traffic data only information from the Avidyne Skytrax100/MLB100 or Freeflight FDL-978-RX
Serial traffic and weather data information from the Avidyne Skytrax100/MLB100 or Freeflight FDL-978-RX
Garmin GTX 345 and other 3rd party compatible ADS-B weather devices transmitting at 38400 baud.
Garmin GTX 335/345 and other 3rd party compatible ADS-B traffic devices transmitting at 38400 baud.
Garmin GTX 345 and other 3rd party compatible ADS-B traffic and weather devices transmitting at 38400 baud.
Serial weather data information from any High Speed Capstone compliant ADS-B device transmitting at 115200 baud.
Serial traffic data information from any High Speed Capstone compliant ADS-B traffic device at 115200 baud.
Serial traffic and weather data information from any High Speed Capstone compliant ADS-B traffic device at 115200 baud.
Serial weather data only for existing MLB100 installs. Serial Freeflight transponder control protocol along with High Speed Capstone ADS-B traffic and weather data information from a Freeflight Ranger device.
Serial transponder control protocol to control an L3 NGT9000R remote mount transponder.
Serial altitude data from the following units: Icarus Instruments 3000 Sandia SAE5-35 Garmin GTX 327 Transponder Trans-Cal Industries IA-RS-232-X, SSD120 ACK Technologies A-30 (Mod 8 and above) Traffic information from a Ryan 9900B, 9900BX, or TAS6XX Series System.
Serial airdata information from the following units: Shadin ADC 200, 200+, 2000
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Selection Shadin-alt
Shadin-fadc
Description
Serial altitude data from the following units: Shadin 8800T, 9000T, 9200T Shadin 9628XX-X Fuel/Air Data Computer Insight TAS 1000 Air Data Computer
Shadin-Fuel
WX-500 TWX
Vhf Ctrl
Serial fuel flow information from the following units: Shadin 91053XP and 91053XT-D "Digiflo-L" Digital Fuel Management Systems Shadin 91204XX(38)D and 91204XT-D "Miniflo-L" Digital Fuel Management Systems JP Instrument EDM-700 or EDM-760 Engine Monitor Other JPI systems (e.g. JPI FS-450) can use this setting but see the specific format guidance from JPI for the Garmin GNS series.
Serial lightning data information from the L3 Communications WX500 Stormscope
Serial lightning data information from the Avidyne TWX670 in "Native" format
Reserved for future VHF remote control
Table 86 RS-232 Input Selection
1 These weather receiving devices are mutually exclusive. Only one source can be displayed at one time. Both weather sources can be wired to the IFD so that the higher priority weather overlay can display on the IFD and the lower priority weather data can be streamed out of the IFD via WiFi for display on a compatible tablet/wireless device application. The current display priority is GDL-69, MLB700, AV300/350, MLB/SkyTrax100.
2 These Traffic receiving devices are mutually exclusive. Multiple devices should not be installed/configured on a single unit.
Channel Outputs
Selection Off
ADS-B (Avi)3
ADS-B+ (G) ADS-B+ (G2)
Aviation3
Description No device(s) connected to output of this channel
Serial position data to the following units: Trig TT31 (V 3.1 or later) Avidyne AXP340 Garmin GTX 330 Low Speed 9,600 Baud
Garmin GTX 335/GTX345/GDL 88 High Speed 38,400 Baud
Serial position, altitude, velocity, and navigation data to the following units: Argus 3000, 5000, or 7000 Moving Map Avidyne FSD Series Garmin MX20 (V5.6 or later), GMX200 Garmin GPSMAP 195, GPSMAP 295 or GPS III Pilot Garmin GPSMAP 196, GPSMAP 296, and GPSMAP 396
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Selection
Aviation no Alt3
AXP322 CrossSync
GDL 691
MLB7001 XMD0761 SkyTrax Trfc2 SkyTrax Trfc+Wx1,2 Capstone Trfc2 Capstone Trfc+Wx1,2 Capstone HS Trfc2 Capstone HS Trfc+Wx1,2 MLB100 Wx1 HW EGPWS3 Freeflight1,2 NGT9000R
Description
Garmin GPSMAP 496, and GPSMAP 696 Garmin Aera 796/795 Garmin GTX 327 Transponder JP Instruments EDM-700 or EDM-760 Engine Monitor Shadin 91204XM Digital Fuel Management System Shadin 91053XP Digital Fuel Management System Shadin 9628XX-X Fuel/Air Data Computer Stormscope Series II (with NAVAID) Moving Map Serial position, velocity, and navigation data to the following units: Garmin MX20 (V5.5 or earlier) Horizon DDMP Insight TAS 1000 Air Data Computer
Select for Avidyne AXP322 Remote Transponder
Serial transfer of flights plans and user waypoints and cross-side data (e.g. Datalink, traffic, lightning, etc) between IFD5XX/4XX units
Note: This is only an option for CHNL 3. Serial data output to a Garmin GDL69/69A P/N 011-00986-00 or 011-00987-00 only (Garmin software version 4.01 or later) pre Avidyne software 10.2.3.1. With software 10.2.3.1 and later P/N 011- 03177-X0 will also work
Serial weather data information to the Avidyne MLB700 and WSI AV-300 / 350
Serial weather data only information to the Avidyne Skytrax100/MLB100 or Freeflight FDL-978-RX
Serial traffic data only information to the Avidyne Skytrax100/MLB100 or Freeflight FDL-978-RX
Serial traffic and weather data information to the Avidyne Skytrax100/MLB100 or Freeflight FDL-978-RX
Garmin GTX 335/345 and other 3rd party compatible ADS-B traffic devices
Garmin GTX 345 and other 3rd party compatible ADS-B traffic and weather devices.
Serial traffic data information from any High Speed Capstone compliant ADS-B traffic device at 115200 baud.
Serial traffic and weather data information from any High Speed Capstone compliant ADS-B traffic device at 115200 baud.
Serial weather data only for existing MLB100 installs.
Serial communication to a Bendix/King KGP 560 EGPWS
Serial Freeflight transponder control protocol along with High Speed Capstone ADS-B traffic and weather data information from a Freeflight Ranger device.
Serial transponder control protocol to control an L3 NGT9000R remote mount transponder.
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Selection MapMX3
Ryan TCAD2
WX-500 TWX
Vhf Ctrl
Description Serial position, altitude, velocity, and navigation data to the following units: Garmin MX20 (V5.7 or later), GMX 200 Traffic information to a Ryan 9900B, 9900BX, or TAS6XXA Series System. Serial communication to L3 Communications WX500 Stormscope Serial communication to the Avidyne TWX670 Reserved for future VHF remote control
Table 87 RS-232 Output Selection
1 These weather receiving devices are mutually exclusive. Only one source can be displayed at one time. both weather sources can be wired to the IFD so that the higher priority weather overlay can display on the IFD and the lower priority weather data can be streamed out of the IFD via WiFi for display on a compatible tablet/wireless device application. The current display priority is GDL-69, MLB700, AV300/350, MLB/SkyTrax100.
2 These traffic receiving devices are mutually exclusive. Multiple devices should not be installed/configured on a single unit.
3 The following RS232 Output protocols may be configured on two or more RS232 ports: Aviation, Aviation No Altitude, ADS-B (avi), HW EGPWS, and MapMx.
7.5.4 Main System Configuration (Page 3)
This is a general page for miscellaneous configurations.
Figure 13 Main System Configuration Page
The Main System Configuration Page (Page 3 of 15) allows the configuration of the following Airframe Options and GPS Parameters on the IFD5XX/4XX.
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Fuel Type Selections: Select Fuel in the Configure field, the following options can be selected:
Selection
Description
Avgas
The aircraft is using Aviation gas (5.967 lbs/gal)
Jet A
The aircraft is using Jet A or Jet A-1 fuel (6.843 lbs/gal)
Jet B
The aircraft is using Jet B (JP-4) fuel (6.467 lbs/gal)
Table 88 Aircraft Fuel Type
GPS Select Selections:
Selection
Description
Auto
In GPS mode on the IFD5XX/4XX, the GPS Select discrete will not be active (open) in a GPS approach, and no messages will annunciate on the IFD5XX/4XX and no pilot action is required. This setting allows the pilot to use the GPS VLOC Capture option on the User Options part of the Setup tab on the AUX page.
Prompt
In dual IFD installations, only the IFD connected to a KFC225 autopilot should be setup for prompt. In GPS mode, the user will be prompted to enable the approach in KFC225 equipped aircraft When Prompt is selected, and a GPS approach mode is active, a CAS message will prompt the pilot to "Enable A/P Approach" on the FPL tab. At that point, the pilot may then enter APR mode on the autopilot. This setting will also ignore the GPS VLOC Capture option on the User Options part of the Setup tab on the AUX page.
Table 89 GPS Sequencing
Airframe Selections:
Selection
Description
Fixed Wing
For Fixed Wing installations
Helicopter
For Helicopter installations
High Speed
For Jet installations
Table 90 Airframe Selection
Tail Number:
Tail number is a text field and is used for various purposes (i.e. Jeppesen data subscription and transponder function).
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External TAWS Selections:
Selection
Description
Yes
Select if an external EGPWS or TAWS device (e.g. KGP 560) is
connected to the IFD5XX/4XX or if you want to turn off the FLTA.
It will disable FLTA and TA functionality as well as aural alerts in
the IFD5XX/4XX
No
Select when no external EGPWS or TAWS device is connected to
the IFD5XX/4XX, thereby enabling all FLTA and TA functionality
on the IFD5XX/4XX.
Table 91 External TAWS Selection
Weight on Wheels (WOW)
Selection
Description
Yes
When set to "Yes" and the Airframe Selection is set to "Helicopter"
Pin 70 on P1001 is used as a discrete input to control the in-air or
on-ground state of the IFD. Logic state required is "low when on
ground"
No
Select "No" when WOW discrete input is unavailable.
Table 92 Weight on Wheels
Checklist Selection Enabled
Disabled
Description
Select Enabled to allow the user editable checklists to be displayed/accessible.
Default setting
Table 93 Checklist Setting
TIS-B Annunciation
Selection
Description
Enabled
Select Enabled for installations in U.S.
Disabled
Outside US airspace
Table 94 TIS-B Annunciations
Joystick Selection Enabled
Disabled
Description
Enables joystick input commands. Controls the automatic creation of user waypoints using external EFIS input. This setting shall be disabled when interfacing to the Proline 21 installations.
Default setting
Table 95 Joystick Input
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Note: It is imperative that only one source of terrain cautions and warnings be enabled on the airplane so as to avoid the potential for conflicting information to be presented to the pilot. If a TAWS system is installed but the IFD's internal TA and FLTA functions are to be used for terrain avoidance, the TAWS system must be fully disabled. If a separate TAWS system is to be used the caution and warning indications generated by the TAWS system can be displayed on a remote third party annunciator and the IFD's TA and FLTA displays and audio must be inhibited. Avidyne TA/FLTA is not an approved TSO-C151 EGPWS unit.
Note: The IFD system supports a Honeywell KGP560/860 system with a remote third party annunciator only. All other external TAWS/EGPWS systems must be disabled if the internal TA and FLTA are to be operational on the IFD system.
7.5.5 Main Input Configuration (Page 4)
The Main Input Page displays information received from ARINC 429, RS-232, and other electrical inputs. This page is helpful during troubleshooting of the IFD5XX/4XX system. This is used for verifying electrical interfaces during installation and troubleshooting.
Field OAT SAT TAT IAS W SPD HDG W DIR GPS SC VLC SC CDI B ALT D ALT P ALT
JOYSTICK WPT
Description Outside Air Temperature Static Air Temperature Total Air Temperature Indicated Airspeed Wind Speed True Heading Wind Direction GPS Selected Course VOR/LOC Selected Course (Not on IFD510/545/410) Status of the CDI Key (Not on IFD510/545/410) Baro Corrected Altitude Density Altitude Pressure Altitude Latitude and longitude of a joystick waypoint sent by an EFIS or Radar indicator
Table 96 Discrete Toggles
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7.5.6 Main Lighting Configuration (Page 5)
The source of the lighting for the IFD5XX/4XX can be the bezel photocell sensor or the dimming bus. 28VDC, 14VDC, 5VDC and 5VAC dimming buses are all supported and are automatically detected by the IFD5XX/4XX.
Figure 14 Main Lighting Configuration Page
Photo Response Time Sets the speed at which the brightness changes when photocell is selected as the lighting source. Both the Bezel and Display fields have a range of 1 to 5, and the factory default is 3. Photo Slope The Photo Slope sets the sensitivity of the display/bezel to changes in the input when the dimming source is the IFD5XX/4XX photocell. This field has a range of 15 to 100, and the factory default is 80. Photo Minimum The Photo Minimum sets the minimum brightness when the dimming source is the photocell. Both the Bezel and Display fields have a range of 1 to 50, and the factory default is 1.
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Photo Maximum
The Photo Maximum sets the maximum brightness when the dimming source is the photocell. Both the Bezel and Display fields have a range of 50 to 100, and the factory default is 100. dimBus Transition %
The dimBus Transition % sets the threshold where the aircraft dimming bus takes over from the photocell. Below this threshold, the aircraft dimmer controls the IFD5XX/4XX lighting. Both the Bezel and Display fields have a range of 0 to 100, and the factory default is 10.
Note: If it is not desired to hand brightness control over to the dimming bus from the photocell at any point, set dimBus Transition % to 0 (zero). Doing so will prevent the scenario where, in increasingly darker environments (e.g. flying past sunset into dark night), the display automatically dims and dims and dims and then suddenly jumps to bright.
dimBus Slope
The dimBus Slope sets the sensitivity of the display/bezel to the aircraft dimmer. Both the Bezel and Display fields have a range of 15 to 100, and the factory default is 60.
Note: Previous to Release 10.1.1.0, a dimBus slope value of 100 on the AviCurve resulted in a maximum brightness value of 21%. In Release 10.1.1.0 and later, a slope value of 100 will result in 100% maximum brightness.
dimBus Minimum
The dimBus Minimum sets the minimum brightness when the aircraft dimmer is the dimming source. Both the Bezel and Display fields have a range of 1 to 50, and the factory default is 1. dimBus Maximum
The dimBus Maximum sets the maximum brightness when the aircraft dimmer is the dimming source. Both the Bezel and Display fields have a range of 50 to 100, and the factory default is 100. dimBus Curve
The dimBus Curve sets the aircraft dimming bus to either a Proportional Curve or AviCurve on the IFD5XX/4XX.
The Proportional Curve tracks the aircraft lighting bus as follows: Maximum night lighting at maximum aircraft lighting bus voltage, Minimum night lighting at minimum aircraft lighting bus voltage (linear in-between).
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The AviCurve tracks the aircraft dimming bus as follows:
Figure 15 Lighting Curve - AviCurve
Figure 16 Lighting Curve - Proportional Curve
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Field Bezel Display Mx Input
Selection
Value displayed represents the current % brightness of the bezel backlighting
Value displayed represents the current % brightness of the display backlighting
Photocell Maintenance Mode will use this method if selected. This is the default setting. This setting uses the Photocell on the IFD5XX/4XX bezel or display.
dimBus Maintenance Mode will use this method if selected. This setting uses the aircraft lighting buss to control the lightning of the bezel or display.
Table 97 Lighting Bus Configuration
Dimming Bus Calibration The section will calibrate the IFD5XX/4XX to the aircraft avionics lighting bus.
Selection dimBus Type
dimBus Max Voltage dimBus Min Voltage
Description
DC select this option if the dimming bus is a DC bus.
AC select this option if the dimming bus is an AC bus.
The IFD needs to know the bus type in order to alter internal configuration as well as properly perform the calibration.
Sets the maximum aircraft dimming bus voltage. Range is 0 28V.
Sets the minimum aircraft dimming bus voltage. Range is 0 28V.
Table 98 Lighting Bus Configuration
To calibrate the dimming bus: 1. Select desired dimBus Type; 2. Select the dimBus Max Voltage field; 3. Push the right bezel knob; 4. Set the dimming bus to the maximum value (e.g. full clockwise position on dimming
rheostat); 5. Push the right bezel knob to store; Repeat the process for the minimum value (use full counter-clockwise position of rheostat)
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IFD5XX/4XX Installation Manual 7.5.7 Main Discrete I/O (Page 6)
This page will test the Main Discrete outputs on the IFD5XX/4XX.
Figure 17 Main CDI/OBS Configuration Page
Selection Verify That
RMT CDI RMT OBS TER INHB RMT RCL
On is displayed when a remote CDI source select switch is pressed. On is displayed when a remote OBS switch is pressed. On is displayed when a remote TERRAIN INHIBT switch is pressed. On is displayed when the COM REMOTE RECALL switch is pressed.
Table 99 External Switch State
Selection
APR GPS INTEG MSG OBS TERM VLOC WPT
Verify That
The APR annunciator is on or off as selected on this page. The GPS source select annunciator is on or off as selected on this page. The INTEG annunciator is on or off as selected on this page. The MSG annunciator is on or off as selected on this page. The OBS annunciator is on or off as selected on this page. The TERM annunciator is on or off as selected on this page. The VLOC source select annunciator is on or off as selected on this page. The WPT annunciator is on or off as selected on this page.
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Selection Verify That
ILS/GPS APR
The ILS/GPS APR output is on or off as selected on this page (NOTE: This output is connected to the autopilot ILS ENGAGE input, not to an annunciation, and therefore this is for bench testing purposes only).
GPS SELECT
The GPS SELECT output is on or off as selected on this page (NOTE: This output is connected to the autopilot GPS SELECT input, not to an annunciation, and therefore this is for bench testing purposes only).
TER CAUT The TER CAUT annunciator is on or off as selected on this page.
TER INHB The TER INHB annunciator is on or off as selected on this page.
TER N/A The TER N/A annunciator is on or off as selected on this page.
TER WARN
The TER WARN annunciator is on or off as selected on this page.
Table 100 Discrete Toggles
7.5.8 Main CDI/OBS Config Page (Page 7)
This page will test the Main CDI/OBS output on the IFD5XX/4XX.
Figure 18 Main CDI/OBS Configuration Page
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The following parameters can be tested: CDI (LAT/VERT)
Selection
Description
Max Left
The remote CDI will be off-scale full deflection to the left/up
Full Left
The remote CDI will be deflected to the left/up
Center
The remote CDI will be centered
Full Right
The remote CDI will be deflected to the right/down
Max Right
The remote CDI will be off-scale full deflection to the right/down
Table 101 Main CDI Test Page
NAV Flag (LAT/VERT)*
Selection
Description
Hidden
The lateral and vertical flag on the external indicator is hidden
In view
The lateral and vertical flag on the external indicator is in view
*This function will only test the low level flags, and does not support the testing of Super Flags
TO-FROM Selection FROM Hidden TO
Table 102 Main CDI Flag Test Page
Description The FROM flag on the external indicator is in view The TO/FROM flag on the external indicator is hidden The TO flag on the external indicator is in view
Table 103 Main CDI Flag Test Page
Selected Course
This section will calibrate the external CDI/HSI to the IFD5XX/4XX.
1. Select 150° on the CDI/HSI;*
2. Verify the Selected Course is displayed on the IFD5XX/4XX and press the ENTR button on the IFD5XX/4XX;
3. After calibrating, verify 30° increments on the CDI/HSI are properly displayed on the IFD5XX/4XX ±2°.
* In order to do the OBS calibration on a KI208A or KI209A, you have to toggle to the "Main Discrete I/O" page, and turn "ON" the GPS discrete toggle. Then turn to the Main CDI/OBS config page (without toggling back to the Discrete I/O page) and calibrate the OBS by dialing 150 degrees on the indicator.
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Ignore Options Selection
Ignore SEL CRS for GPS
Ignore SEL CRS for VLOC
(N/A for IFD510/545/410)
CDI Selection Selection GPS
VLOC
(N/A for IFD510/545/410)
GPS Only
(N/A for IFD510/545/410)
Description Yes/No Nav Source knob used in OBS. Yes = ignore analog or 429 selected course. OBS mode then uses the Nav Source knob to dial the course. Yes/No Yes = Lateral navigation flag displays VOR validity, deviation data for VOR is always centered. No = deviation and flag data is based on OBS selection.
Table 104 Ignore Options Selection
Description The GPS is the navigation source. The GPS annunciator will also be active. This is the setting for IFD510/545/410 The VLOC is the navigation source. The VLOC annunciator will also be active.
The VLOC selection on the IFD5XX/4XX Nav Source knob has been disabled. Therefore, GPS and OBS are the only two available choices via the IFD5XX/4XX Nav Source knob
Table 105 CDI Source Selection
OBI Source Selection
Always GPS Track CDI V-Flag State Selection Declutter
Normal
Description The MAIN Serial OBI output will always be selected to GPS. The MAIN Serial OBI will track the Nav Source knob selection.
Table 106 OBI Source Selection
Description The vertical deviation bar will be in parked in the maximum UP position when the vertical flag is removed, except in the following cases:
· VLOC is selected on the Nav Source knob and an ILS frequency is tuned (N/A for IFD510/545/410)
· GPS is selected on the Nav Source knob and valid GPS approach is active (precision GPS with vertical guidance)
The vertical deviation bar will be in the center position when vertical navigation is invalid and the vertical flag will be present.
Table 107 V-Flag State
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IFD5XX/4XX Installation Manual 7.5.9 VOR/LOC/GS CDI (Page 8)
Note: This page is not applicable for the IFD510/545/410. This will test the operation of the VOR/LOC/GS output from the IFD5XX/4XX on the P1006 connector to an external CDI/HSI display.
Figure 19 CDI Test Page
Note: This page currently will only test low level flags and does not support the testing of super flags
CDI (LAT/VERT)
Selection
Description
Max Left
The external CDI will be off-scale full deflection to the left/up
Full Left
The external CDI will be deflected to the left/up
Center
The external CDI will be centered
Full Right
The external CDI will be deflected to the right/down
Max Right
The external CDI will be off-scale full deflection to the right/down
Table 108 Navigation CDI Test Page
NAV Flag (LAT/VERT)
Selection
Description
Hidden
The lateral and vertical flag on the external indicator is hidden
In view
The lateral and vertical flag on the external indicator is in view
Table 109 Navigation Flag Test Page
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SPR Flag (LAT/VRT Super Flag)
Selection
Description
Hidden
The lateral and vertical flag on the external indicator is hidden
In view
The lateral and vertical flag on the external indicator is in view
Table 110 NAV Superflag Test Page
TO-FROM Selection FROM Hidden TO
Description The FROM flag on the external indicator is in view The TO/FROM flag on the external indicator is hidden The TO flag on the external indicator is in view
Table 111 Navigation TO/FROM Page
Selected Course
This section will calibrate the external CDI/HSI to the IFD5XX/4XX.
1. Select 150° on the CDI/HSI;*
2. Verify the Selected Course is displayed on the IFD5XX and press the ENTR button on the IFD5XX/4XX;
3. After calibrating, verify 30° increments on the CDI/HSI are properly displayed on the IFD5XX/4XX ±2°.
* In order to do the OBS calibration on a KI208A or KI209A, you have to toggle to the "Main Discrete I/O" page and turn on the GPS discrete toggle. Then turn to the Main CDI/OBS config page (without toggling back to the Discrete I/O page) and calibrate the OBS by dialing 150 degrees on the indicator
DME Channel Mode
This configuration allows you to set the format for the DME tuning data output.
Selection
Description
UNINSTALLED No DME installed/configured
King Serial
King Serial DME tuning
Parallel 2x5
2 of 5 parallel DME tuning
Parallel BCD Shifted BCD (Binary Coded Decimal) parallel DME tuning
Parallel Slip
Slip-code parallel DME tuning
Narco 890/891
2 of 5 parallel DME tuning, compatible with the following DME units:
Narco DME 890
Narco DME 891
ARC (Cessna) RTA-476A
Table 112 DME Channel Mode
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IFD5XX/4XX Installation Manual 7.5.10 VOR/LOC/GS ARINC 429 Configuration (Page 9)
Note: This page is not applicable for the IFD510/545/410. This page will configure the ARINC 429 for the VOR/LOC/GS output.
Figure 20 VOR/LOC ARINC 429 Configuration Page
The following parameters can be configured.
Speed:
Selection
Description
Low
Standard Low-speed ARINC 429
High
High-speed ARINC 429
Table 113 VOR/LOC/GS ARINC 429 Speed Configuration
Format: Selection VHF 429
VHF/GPS 429
Description
Standard VOR, Localizer, Glideslope, and Frequency information
Standard VOR, Localizer, Glideslope, Frequency information as well as Pseudo Localizer and Pseudo Glideslope during GPS approach with CDI set to GPS.1
Table 114 VOR/LOC/GS ARINC429 Format Selection
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SDI: Selection Common VOR/ILS 1
VOR/ILS 2
DME Mode:
IFD5XX/4XX Installation Manual
Description RX: Accepts all 429 inputs TX: Generates all 429 outputs with SDI =0 Number 1 (Pilot) VOR/ILS Receiver RX: Accepts 429 inputs with SDI = 0 or 1 TX: Generates all 429 outputs with SDI = 1 Number 2 (Copilot) VOR/ILS Receiver RX: Accepts 429 inputs with SDI = 0 or 2 TX: Generates all 429 outputs with SDI = 2
Table 115 VOR/LOC/GS SDI Selection
Selection Directed Freq 1
Directed Freq 2
Description
If the IFD5XX/4XX is connected to a single-channel or multichannel ARINC429 DME, Direct Freq 1 will channel Receiver 1.
If the IFD5XX/4XX is connected to a multi-channel ARINC429 DME, Direct Freq 2 will channel Receiver 2
Table 116 DME Mode Selection
7.5.11 GPS Vertical Offset (Page 10)
This page will configure the GPS Receiver for the antenna offset on the aircraft and designate if the IFD5XX/4XX will use the WAAS functionality of the system.
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Figure 21 GPS Antenna Setup
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Measure the distance from the ground to the top of the GPS antenna to nearest tenth of a foot, as shown in the image below, and enter the value into the IFD5XX/4XX (to the nearest 1/10th foot).
Figure 22 GPS Height
7.5.12 GDL Configuration Pages (Page 11)
This page allows the configuration of the Garmin GDL 69/69A. This page is always displayed in Maintenance Mode. The GDL 69/69A must be activated prior to configuring the IFD5XX/4XX, reference the GDL installation manual for setup and configuration information.
Figure 23 GDL Configuration Page
GDL Selection Page
This page selects the attenuation and the type of GDL receiver connected to the IFD5XX/4XX.
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Selection Attenuation
Model
Description
This parameter sets the attenuation GDL 69/69A. Reference the Garmin GDL69/69A installation manual for more information.
This parameter sets the model to either GDL 69 (weather only) or GDL 69A (weather and audio) models.
Table 117 GDL Selection Page
Note Compatibility with P/N 011-00986-00 or 011-00987-00 only pre software 10.2.3.1. With software 10.2.3.1 or higher P/N 011-03177-X0 will also function
Note: If the GDL69/69A is connected to any other display in the aircraft, this attenuation setting must be set to match them
7.5.13 Remote XPDR Configuration (Page 12)
This page will configure the Avidyne AXP322 Remote transponder. Reference the AXP322 installation manual as needed. The transponder must be configured to operate.
Please note; it may take up to 3 minutes to update the transponder configuration after changing a parameter below.
A dual AXP322 transponder installation will require that this function is performed on both transponders
Selection Hex Code A/C Width A/C Length GPS Lin. Offset 1090 MHz Receiver UAT Receiver Squat Input
A/C Class
Description
Enter the aircraft's Mode S Address issued by the registration authority. This code must be entered as a hexadecimal value.
Enter the aircraft's width in meters
Enter the aircraft's length in meters
Enter the distance from the front of the aircraft to the GPS antenna in meters
Enter "Yes" if the aircraft is equipped with 1090 MHz ADS-B In receiver
Enter "Yes" if the aircraft is equipped with UAT ADS-B In receiver
For ADS-B out compliance, a squat switch is required for automatically selecting the transponder air or ground mode of operation. For aircraft without a squat switch, connect the squat switch input of the transponder to P1001 pin 8 of one of the IFD5XX/IFD4XX for IFD's with software 10.0.0 or higher. In either case, set the transponder to "Avidyne" when performing the squat switch setup.
Enter the aircraft category
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Selection A/C Speed GPS Lat. Offset Certification
Description
Enter the aircraft speed
Enter the lateral distance in meters for the GPS antenna
VFR installations, aircraft with a non-WAAS antenna (reference Section 7.5.11), or unapproved ADS-B out installations must set this field to "uncertified". All other installations reference the Avidyne AXP322 installation manual for certification level.
Table 118 Remote XPDR Configuration Selections
7.5.14 Network (WiFi) Setup (Page 13)
If the IFD is equipped with the optional Wi-Fi and Bluetooth options, configuration of these interfaces may be desired using the WiFI Configuration Page in Maintenance Mode.
7.5.14.1 Wi-Fi Configuration
The IFD Wi-Fi system can be configured in one of two ways. The IFD may operate as a Wi-Fi access point (WAP) or can connect to an external access point provided by another accessible device.
NOTE: The IFD Maintenance mode refers to a WAP configuration as "Local". Similarly, Maintenance mode refers to a configuration in which the IFD connects to a separate access point as "Remote".
NOTE: The IFD Maintenance page Network Configuration offers Mode options that include Local Wired, Remote Wired DHCP and Remote Wired Static. These options are not applicable to installations approved by the IFD4XX/IFD5XX AML STC SA00343BO. Please contact Avidyne Customer Service for additional details on these interfaces.
When configuring the IFD as a WAP, it is necessary to define the SSID (i.e. the name of the network) and a PSK (i.e. the network password). The factory default settings are "LIO_WIFI" for the SSID and "abcdef1234" for the password. When configured as a WAP, the IFD ignores the IP address field. In order to configure the IFD as a WAP, proceed as follows:
To configure the Mode 1. Boot the IFD to Maintenance mode. 2. Select the "Config" tab. 3. Turn the right knob until the "Network Configuration" Page is displayed as shown in the image below.
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Figure 24 Network Configuration Page
4. If the "Mode" value is not set to "Local WiFi", press the lower right knob and use the outer knob to select the mode value. a. Once selected, use the inner knob to change the value to "Local Wi-Fi" b. Press the knob again to exit edit mode.
To configure the network name (SSID) 1. Boot the IFD to Maintenance mode. 2. Select the "Config" tab. 3. Turn the right knob until the "Network Configuration" Page is displayed as shown in the image below.
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Figure 25 Network Configuration Page
1. Press the lower right knob 2. Using the outer right knob, advance the selection rectangle until the current SSID
field is selected as shown:
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Figure 26 Network Configuration Page
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4. Press the right knob 5. The inner knob can now be used to advance through the available characters. The
outer knob will advance to the next character in the name. NOTE: One of the possible character selections is a space character. Spaces at the end of the name will not be contained in the final name. In other words, "NAME<SP><SP>" will present a network name of "NAME". 6. Press the right knob to complete the edit
To configure the network password (PSK) 1. Boot the IFD to Maintenance mode. 2. Select the "Config" tab. 3. Turn the right knob until the "Network Configuration" Page is displayed as shown in the image below.
Figure 27 Network Configuration Page
1. Press the lower right knob 2. Using the outer right knob, advance the selection rectangle until the PSK field is
selected as shown:
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Figure 28 Network Configuration Page
4. Press the right knob
5. The inner knob can now be used to advance through the available characters. The outer knob will advance to the next character in the PSK.
NOTE: One of the possible character selections is a space character. Spaces at the end of the PSK will not be contained in the final PSK. In other words, "PASSWORD<SP><SP>" will present a network PSK of "PASSWORD".
NOTE: Non empty PSKs must contain at least 8 characters. If there are fewer than 8 characters, the system will fill missing characters with a '?' character.
NOTE: Empty PSKs are allowed though not recommended.
6. Press the right knob to complete the edit.
7.5.14.1.1 Configuring the IFD as a Client to an External WAP
In some cases, an aircraft may have an existing WAP in use. For example, some aircraft may be accustomed to connecting 3rd party iPad applications to a Stratus ADS-B receiver. These pilots will likely wish to also have access to the IFD from their iPads. In order to achieve this configuration, the IFD must be configured to connect to the Stratus receiver. This will allow tablet devices to access data from both the Stratus and the IFD simultaneously.
To configure the Mode 1. Boot the IFD to Maintenance mode. 2. Select the "Config" tab. 3. Turn the right knob until the "Network Configuration" Page is displayed as shown in the image below.
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Figure 29 Network Configuration Page
4. If the "Wifi Mode" value is not set to "Remote", press the lower right knob and use the outer knob to select the mode value. a. Once selected, use the inner knob to change the value to "Remote Wi-Fi" b. Press the knob again to exit edit mode.
Designate the Network to Connect To: 1. Boot the IFD to Maintenance mode. 2. Select the "Config" tab. 3. Turn the right knob until the "Network Configuration" Page is displayed as shown in the image below.
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Figure 30 Network Configuration Page
1. Press the lower right knob 2. Using the outer right knob, advance the selection rectangle until the SSID field is
selected as shown:
Figure 31 Network Configuration Page
4. Press the right knob
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5. The inner knob can now be used to advance through the available characters. The outer knob will advance to the next character in the name. Set this field to the name of the remote network to which you wish to attach. This will be provided by the device that supplies the network.
6. Press the right knob to complete the edit.
Configure the network password (PSK) NOTE: This value will be supplied by the device to which you are attempting to connect.
1. Boot the IFD to Maintenance mode. 2. Select the "Config" tab. 3. Turn the right knob until the "Network Configuration" Page is displayed as shown in
the image below.
Figure 32 WiFi Configuration Page
1. Press the lower right knob 2. Using the outer right knob, advance the selection rectangle until the Remote PSK
field is selected as shown:
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Figure 33 Network Configuration Page
1. Press the right knob 2. The inner knob can now be used to advance through the available characters. The
outer knob will advance to the next character in the PSK. NOTE: One of the possible character selections is a space character. Spaces at the end of the PSK will not be contained in the final PSK. In other words, "PASSWORD<SP><SP>" will present a network PSK of "PASSWORD". NOTE: Non empty PSKs must contain at least 8 characters. If there are fewer than 8 characters, the system will fill missing characters with a '?' character. NOTE: Empty PSKs are allowed though not recommended. NOTE: IP address field is unused with this option. Press the right knob to complete the edit
7.5.15 Bluetooth Setup (Page 14)
7.5.15.1 Configuring the Bluetooth Interface
1. Boot the IFD to Maintenance mode. 2. Select the "Config" tab. 3. Turn the right knob until the "Bluetooth Setup" Page is displayed as shown in the
image below.
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Figure 24 Bluetooth Setup Page
4. Once initialized, the page will present a button on the left side reading "Start Scan". Press this button to allow the system to find all discoverable Bluetooth devices in range of the IFD.
NOTE: You will likely need to put the Avidyne Bluetooth keyboard into discoverable mode by pressing the button on the rear of the keyboard. 5. Once the device you wish to pair with appears in the list presented on the IFD screen, press the "Stop Scan" button if the scan has not yet completed. 6. Select the device of interest but using the outer ring of the lower right knob. 7. Press "Pair Device" a. You will now be prompted to enter a number and press ENTER.
b. Enter the specified number on the Avidyne Bluetooth Keyboard and then press the keyboard's ENTER key.
7.5.16 IRU Calibration, IFD545, IFD550 (Page 15)
In order to calibrate the IFD550 or IFD545 you must access the IRU Calibration page. This page can be found by:
1. Entering maintenance mode. 2. Accessing the Config tab by pressing the right side of the AUX key. 3. Turn the outer right knob until you see the IRU Calibration page (see picture below).
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Figure 25 IRU Calibration Page
IFD550 and IFD545 IRU require minimal calibration. The adjustment parameters available and their impact on the system behavior is discussed below.
In order to adjust each of the parameters, you will press the right knob until the cursor advances to the value to be set. Use the inner knob to adjust the value.
Once all settings have been adjusted as desired, press the "Save Offsets" LSK to save the values you have configured.
7.5.16.1 Setting TAS:
Press the right knob until the cursor advances and the TAS field is selected. Turn the right knob to change the value until it represents the cruise airspeed of the aircraft in knots. Look in the POH and set the TAS value to the 75% power at 6,000 ft. value. NOTE: Setting of the TAS value is mandatory.
7.5.16.2 Adjusting Pitch Roll and Yaw
Your installation may not require the setting of pitch, roll and yaw values. These values need only be set if the installation orientation of the IFD545/IFD550 is not aligned with the lateral, vertical or longitudinal lines of the aircraft (see diagram below).
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Figure 26 Calibration Line Locations
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7.5.16.2.1 Adjusting Pitch
For installations in which the IFD system is not at a right angle with respect to the horizontal axis of the aircraft, the Pitch value will need to be adjusted. If the rear of the IFD is pitched down with respect to the horizontal axis of the aircraft, you will need to enter a negative number for the Pitch value. If the rear of the IFD is pitched up with respect to the horizontal axis of the aircraft you will need to enter a positive number for Pitch.
7.5.16.2.2 Adjusting Roll
For installations in which the IFD system is not aligned with the lateral line of the aircraft, the roll value needs to be adjusted. If the IFD is tilted toward the left wing of the Aircraft, you will need to enter a positive number for the Roll value. If the IFD is tilted toward the right wing of the Aircraft, you will need to enter a positive number for the Roll value.
7.5.16.2.3 Adjusting Yaw
For installations in which the IFD system is not parallel to the longitudinal line of the aircraft, the yaw value will need to be adjusted. If the rear of IFD is skewed to the right of longitudinal line, then you will need to enter a positive number for the Yaw value. If the IFD is skewed to the left of longitudinal line, you will need to enter a negative number for the Yaw value.
7.5.16.3 Post Calibration Check
Once you have entered all calibration values as desired, boot the IFD into flight mode. Press the SVS button to display the synvis screen. The display should accurately reflect the aircraft orientation. If this is not the case, readjust the Pitch, Roll and Yaw settings as described above.
7.5.17 RDR2000 Radar Configuration (Page 16)
7.5.17.1 Configuration Module Setup
7.5.17.2 Primary Radar Setup
1. Power on the primary IFD in Maintenance Mode and select the Config/Radar Calibration page.
2. Press the "Radar" LSK, then place the radar into "Test" 3. Press the Diagnostics LSK to display the diagnostics page. 4. Press the Knob-Func LSK until "Gain" is selected 5. Turn the left inner knob counter-clockwise until `Gain Pot' displays -31.0 6. Press the Knob-Func LSK until "Tilt" is selected 7. Turn the left inner knob clock-wise until "15.00°" is displayed in the "Tilt Setting" field. 8. Press the Diagnostics LSK to return to the standard radar page. 9. Adjust the left outer knob to select a range of 240 NM. 10. Press the "Diagnostics" LSK to return to the diagnostics page. Six Yellow faults shall
quickly flash several times and then "-none-" shall be displayed. This confirms that the radar has been placed into calibration mode.
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7.5.17.3 Antenna Clearance Check
Set the Knob-Func LSK back to `Gain' then turn the left inner knob clock-wise to obtain a value between -26.5 and -28.0 in the "Gain Pot" field. This will initiate the antenna clearance scan. The antenna will move to each of the extreme positions to determine that there is no interference with the antenna movement and all scan motors are working properly.
7.5.17.4 Radar Stabilization (IFD545, IFD550 only)
1. For stabilization ARINC labels outputs to become active, check the stabilization box "ON"
7.5.17.5 Calibrate Radar Pitch and Roll
1. Set the Knob-Func LSK to `Roll Trim'. 2. Rotate the left inner knob to adjust the "Roll Trim" setting to "0.000°". 3. Level the aircraft. 4. Set the Knob-Func LSK to `Gain' and rotate the left inner knob to obtain a value between
-11 and -12. This will allow adjustment of the "Pitch Angle". 5. Set the "Pitch Angle" to 0.0° +/- 1.0 degrees as follows:
a. Set the Knob-Func LSK to `Tilt'. b. To increment the value of the "Pitch Angle" use the left inner knob to select a
"Tilt Setting" between 5 and 10. When the "Tilt Setting" is between 5 and 10, the value of the "Pitch Angle" field will slowly increase. c. To decrement the value of the "Pitch Angle" use the left inner knob to select a "Tilt Setting" between -5 and -10. When the "Tilt Setting" is between -5 and -10, the value of the "Pitch Angle" field will slowly decrease. d. When the desired setting is reached, quickly adjust the "Tilt Setting" to above 10 or below -10 to "lock in" the setting. 6. Set the Knob-Func LSK to `Gain' and rotate the left inner knob to obtain a value between -7 and -9. This will allow adjustment of the "Roll Angle". 7. Set the "Roll Angle" to 0.0° +/- 1.0 degrees as follows: a. Set the Knob-Func LSK to `Tilt'. b. To increment the value of the "Roll Angle" use the left inner knob to select a "Tilt Setting" between 5 and 10. When the "Tilt Setting" is between 5 and 10, the value of the "Roll Angle" field will slowly increase. c. To decrement the value of the "Roll Angle" use the left inner knob to select a "Tilt Setting" between -5 and -10. When the "Tilt Setting" is between -5 and -10, the value of the "Roll Angle" field will slowly decrease. d. When the desired setting is reached, quickly adjust the "Tilt Setting" to above 10 or below -10 to "lock in" the setting. 8. To save the changes into the radar perform the following steps: a. Set the Knob-Func LSK to `Gain' and rotate the left outer knob to obtain a "Gain Pot" setting between -4 and -5. b. The "Faults" field shall display "Gyro Input". c. Set the Knob-Func LSK to `Tilt' then change the "Tilt Setting" to -15.00°. The "Faults" field shall flash indicating that the calibrations settings have been saved.
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If the save procedure is successful the "Gyro Input" fault will be removed and the "Scan Angle" will cycle through the entire number range. A "transmitter inhibit" fault shall be displayed in the "Faults" field.
7.5.18 Stormscope Test Page (Page 17)
The Maintenance Mode Stormscope Test page is accessible from the Maintenance Mode Config Tab when one set of the RS232 ports has been configured as WX-500 and at least one power cycle has been executed since configuration. Stormscope Test page contains the following LSKs: Change Mode, Strikes Clear, Get Data
Change Mode LSK - Changes to the Stormscope test mode as shown in the LSK. The mode selected will be returned by the WX-500 and will display within the strike display. Repeated presses of the Change Mode LSK will step through each of the modes, cycling back to the first mode in the list (Weather). These are the Stormscope test modes:
· Weather - basically a fixed heading version of normal flight mode - will display real lightning strikes if any are generated.
· Noise - similar to Weather mode but with the WX-500 sensitivity set to determine where excess noise might be generated.
· Strike Test - a target displaying test strikes as generated by a WX-500 strike generating test set.
· Demo - similar to Weather mode with the strikes generated internally by the WX500's Demo mode.
· Self-Test - executes the WX-500 internal Self-Test sequence which will return to Weather mode after 10 seconds.
Strikes Clear LSK - Pressing this LSK will send a "clear strikes" command to the WX-500, clearing its internal buffer of strikes.
Get Data LSK -Pressing the Get Data LSK will Download Data from the WX-500. The Stormscope Downloadable Data page will display ASCII data as retrieved verbatim from the Stormscope. Repeated presses of the Get Data LSK will step through each of the Downloadable Data modes, cycling back to the first mode in the list (SW Version). These are the Stormscope Downloadable Data modes:
· SW Version - displays the WX-500 Main SW Version / Main Boot SW Version / DSP SW Version
· Config - displays the WX-500 configuration settings (Serial Jumpers, Hdg Valid Flag, Flag Sense, Hdg Value, Inhibit Line and Antenna Mount).
· Environment - displays the WX-500 environmental parameters (voltages and processor temp)
· Fault Log - displays the WX-500 fault log history of the last 20 faults. d.
7.5.19 GAD 42 Configuration
The IFD5XX/4XX can be connected to the Garmin GAD42 Interface Adapter but there is no dedicated GAD42 configuration page in the IFD5XX/4XX.
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If the IFD5XX/4XX is replacing a GNS530/W or GNS430/W that had previously been connected to a GAD42, then no action is required since the configuration is already saved in the GAD42. If this is a new installation of an IFD5XX/4XX (i.e. not replacing an existing GNS530/W or GNS430/W) or if the GAD42 had to be replaced for service, then the GAD42 must be configured via a manual strapping method as described in Garmin P/N 190-00159-00 GAD42 Installation Manual, Section 5.1. If the IFD5XX/4XX displays a "GAD 42 Needs Service" message, return the GAD 42 unit to the manufacturer.
7.5.20 Other System Diagnostics Pages
The IFD provides other miscellaneous diagnostics pages that are shown here for reference. Each page variant is accessed by pressing the L4 LSK labeled "Info".
Figure 27 Hardware Version Page
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Figure 28 Software Version Page
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Figure 29 Fan Status Page
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Figure 30 IFD Temperature Status Page
The pages on the "Diag" tab are for Avidyne Service Center diagnostics purposes and are not described in this manual.
7.6 Checkout
After configuring the IFD5XX/4XX, the following post-installation tasks should be performed.
7.6.1 Database Check
Verify the Navigation, Chart, and Obstacle databases are up-to-date. If the databases need to be updated, reference the IFD5XX/4XX Pilot's Guide or Section 10.1 for update procedures.
7.6.2 Airplane Flight Supplement Check
Complete and install the IFD5XX/4XX Airplane Flight Manual Supplement in the aircraft's Flight Manual or Pilot's Operating Manual.
7.6.3 Instructions for Continued Airworthiness
Complete and install the IFD5XX/4XX Instruction for Continued Airworthiness in the aircraft maintenance records.
7.6.4 Aircraft Weight and Balance
Update the Aircraft's Weight and Balance in the aircraft records. For those installations where an IFD5XX/4XX is replacing a similar equipped GNS530 or GNS430 (a like variant) no weight and balance must actually be performed. If a GPS only
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Garmin unit is being replaced with a full featured IFD5XX/4XX, the weight change is more than one pound and a weight and balance must be prepared. Since a full featured IFD5XX/4XX is within 5% of the weight of the removed GNS530/430 (less than 1 pound difference), no new weight and balance must actually be performed according to AC 43.13-1B Change 1 Acceptable Methods, Techniques, and Practices Aircraft Inspection and Repair (Chapter 10) and AC 120-27E Aircraft Weight and Balance Control.
7.6.5 Electrical Load Analysis
Verify the aircraft's electrical load is within limits, reference Section 4.10.
7.6.6 GPS Signal Acquisition
After installation, position the aircraft outside with clear unobstructed view of the sky. Verify the IFD5XX/4XX acquires and calculates a GPS position. Verify no interference from other aircraft equipment is observed (e.g. TCAS, SATCOM, etc)
7.6.7 VHF COM Checkout
Note: This section is not applicable for IFD510/545/410. 7.6.7.1 VHF COM Interference
After installation, the VHF Communication should be tested. In 1 MHz increments between 118-136.000 MHz, transmit for 35 seconds on each frequency. Verify, no interference between VHF Comm and other aircraft systems. Evaluate the GPS system on the following frequencies. The GPS system should not experience complete signal loss on when transmitting on the VHF Comm.
25 kHz channels · 121.150 · 121.175 · 121.200 · 131.250 · 131.275 · 131.300
8.33 kHz channels · 121.185 · 121.190 · 130.285 · 131.290
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7.6.7.2 VHF Antenna Checkout
Verify the VSWR is less than 2:1 through the entire frequency band. This can be verified using an aviation navigation test set (e.g. IFR 4000 or similar test equipment). VSWR higher than 2:1 will have reduced VHF Communication performance. If >2:1 VSWR, verify in-flight performance is acceptable.
7.6.7.3 Receiver/Transmitter Operation
Test VHF Com's ability to receive and transmit to another VHF Com station. Verify using a low/middle/high frequency.
7.6.8 VOR/LOC/ GS Checkout
Note: This section is not applicable for IFD510/545/410. If installed, test the VOR/LOC/GS system using a local frequency or test set. Verify the OBS (selected course) is functioning, CDI/HSI/PFD is indicting correctly, and NAV audio is received. Also, verify no EMI on the VOR/LOC/GS system.
7.6.9 Autopilot
If the IFD5XX/4XX can be coupled to an Autopilot system, verify the Autopilot is operating correctly with the IFD5XX/4XX as the navigation source.
7.6.10 Magnetic Compass Swing
After installation and EMI checks are complete, perform a magnetic compass "swing" in accordance with the aircraft installation manual for updating the heading correction card in accordance with 14 CFR 23.1327 and 23.1547.
7.6.11 IFD5XX/4XX Bezel and Display Lighting
Verify the Bezel and Display Lighting for the IFD5XX/4XX can be set to an appropriate level for Day and Night flight conditions. Likewise, verify any external HSI/CDIs can be properly adjusted for day and night lighting conditions.
7.6.12 External Annunciators and Switches
If installed, verify external annunciators and switches are operating correctly. Verify the external annunciator lighting can be adjusted for Day and Night flight conditions (Bright and Dim setting, but never off). Verify all external switches are functioning correctly.
7.6.13 Placards
Verify all circuit breaker(s), switches, and limitation placards (if needed) are installed. If required per Section 2.4.1, there must be a placard in clear view of the pilot that specifies the kind of operations to which the operation of the airplane is limited or from which it is prohibited under 14 CFR 23.1525. The limitation placard must be installed in a conspicuous place in the Pilot's field of view. The placard text height must be a minimum of 0.10 inches in contrasting color to the surrounding area. The text must be high-quality solid-color font of at least 300 DPI (dots per inch). The placard must not be easily disfigured, erased, or obscured.
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7.6.14 Self-test Page
For the duration that the notification of legal rights page is displayed during normal power up on the ground, all remote annunciator lamps are lit up and the system generates a specific set of electrical outputs for the purpose of self-test and troubleshooting. The table below defines the outputs transmitted during this time.
Parameter Course Deviation
Glideslope/Vertical Deviation Annunciators Bearing to Waypoint (RMI) Selected Course (OBS)
Desired Track Distance To Go Time To Go Active Waypoint Groundspeed Present Position Waypoint Alert Phase of Flight Message Alert GPS Integrity Roll Steering (if applicable)
Self-test Value
Half-scale left deviation, TO indication, flag stowed
Half-scale up deviation, flag stowed
All on
135°
150° when interfaced to an HSI with course pointer
150°
10.0 NM
4 minutes
"AVDYN"
150 knots
N39°04.05', W094°53.86'
Active
Enroute
Active
Invalid
Flight Director commands 0° bank (level flight) for 5 seconds; commands increasing right bank at 1°/second for 5 seconds; commands 5° right bank for 5 seconds; commands decreasing right bank at 1°/second for 5 seconds, until command is 0° bank again. This cycle repeats continuously.
Table 119 Self-test Output
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7.6.15 Dual IFD5XX/4XX Configuration
If installing two IFD5XX/4XX units, verify duplex communication between the two units. Reference Section 3.3.8 and 7.3 for limitations and configuration.
7.6.16 Heading Interface Check
Verify the IFD5XX/4XX is receiving heading information from an external source. This can be verified on the Main Input Page in maintenance mode, reference Section 7.5.5. If power is removed from the external heading source, the Main Input Page will display dashed lines for heading. Note: If the IFD5XX/4XX is connected to a Primary Flight Display, it must be turned off before performing this check.
7.6.17 ADS-B Output
If the IFD5XX/4XX is connected to ADS-B out transponder, verify the position information transmitted is correct per 14 CFR 91.227. Also, if using the IFD5XX/4XX for transponder Mode-C altitude information, verify the transponder is using the correct altitude source from the IFD5XX/IFD4XX, reference Section 6.12.
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8. Flight Checks
The IFD5XX/4XX must be flight tested to verify the installation is operating properly. The following items should be tested in flight to verify the IFD5XX/4XX function.
8.1 GPS Verification
Verify the following in flight: · Verify the GPS reception during all phases of flight. (e.g., bank angles of up to 30 degrees and pitch angles associated with take-off, departures, landing and missed approaches) · Verify the following GPS/FMS operation: · Hold at a designated waypoint · Intercept and track to or from a waypoint on a selected course · Waypoint sequencing · Verify the overall operation of procedures or paths · Selection of an approach · Evaluate the display of navigation parameters on the flight instruments (PFD, HSI, CDI) is correct · Verify annunciation is correct and in the Pilot's field of view
8.2 VHF COM Flight Check
Note: This section is not applicable for IFD510/545/410. Verify in-flight the IFD5XX/4XX VHF communication transceiver in the high, mid, and low frequency ranges. Verify the VHF at least 50 nautical miles and at an appropriate altitude.
8.3 VOR Flight Checks
Note: This section is not applicable for IFD510/545/410. Verify in-flight the IFD5XX/4XX VHF navigation receiver by tuning a local VOR station within 50 nautical miles. Verify the audio tone is heard and course deviation information and flag information is correct.
8.4 ILS Flight Checks
Note: This section is not applicable for IFD510/545/410. Verify in-flight the IFD5XX/4XX VHF navigation receiver by tuning an airport with an ILS. Verify the NAV ID audio tone is heard and the course deviation and flag information is correct.
8.5 Autopilot Checks
Verify the IFD5XX/4XX interface to the autopilot is correct. Reference the Autopilot Manual installation/maintenance manual for test procedures. Verify the following functions:
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· Evaluate the steering response while in Flight Director (FD) and when the autopilot is coupled
· Execute several fly-by-turns with varying wind conditions for the FD and autopilot
· Evaluate the autopilot's response to a GNSS fault (e.g., pulling the IFD5XX/4XX Circuit Breakers)
8.6 Sensors Verification
Verify the IFD5XX/4XX interface to other aircraft sensors are operating correctly (e.g., Traffic, Lightning, Weather, etc).
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9. Glove Validation Procedures
Many types of gloves can be used with the IFD touch screen display. The key parameter for the effectiveness of a glove with touch screen is the distance between the finger and the glass and to a lesser extent, the type of material separating the skin from the glass. The thinner the glove or the more compatible the material (e.g. leather, fine cotton, etc), the greater the likelihood of success will be. Likewise, the more surface area that comes in contact with the glass, the greater the success may be. Each glove must be qualified for compatibility with the display and those glove calibration procedures (specific to the glove and the pilot combination) are immediately below. If all verification steps are marked as a "Pass" then the glove/pilot combination is considered to be a qualified pair.
Pilot Name
Description of Glove
Verification Step
Touch the standby frequency window and verify a virtual keyboard is displayed.
Circle
one
Pass
Fail
Type 121.7, press the "ENTER" button on
the virtual keyboard and confirm
121.700 is the displayed frequency in the
#1 Standby Com window.
Pass
Fail
Press each of the page tabs displayed on
the present page and verify the IFD
changes to the selected tab.
Pass
Fail
With the FMS FPL tab displayed, use
touch to type in a typical flight plan and
verify that all entries were recognized.
Pass
Fail
With the Map page and tab displayed, attempt to pan the map.
Pass
Fail
With the Map page and tab displayed, attempt to pinch zoom (in or out) the map to produce a range change.
Pass
Fail
With the Map page and tab displayed,
attempt to graphically flight plan
("rubber band") and verify the intended
change was made.
Pass
Fail
Press the "Freq" function key on the bezel and then double tap a frequency from the list to place it into the #1 standby slot.
Pass
Fail
Table 120 Glove Validation Procedure
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10. Software and Database Update Procedures
10.1 Data Updates
Periodic updates to navigation data, charts data, and obstacle data are all made through the USB port on the front of each IFD. Updates must be performed in accordance with 14 CFR Part 43, Appendix A (c) and FAA AC 20-153( ) paragraph 11.
The table below summarizes the databases update periods:
Database Chart Data
Update Cycle
14 days
Nav Data
Obstacle Data
Terrain Data
28 days 56 days
As required
Comments & Source
Expiration watermark displayed after 14 days indefinitely until data updated (Jeppesen) (N/A for IFD4XX)
Airport, airway, navaid, airspace, and FMS data (Jeppesen)
Displayed on map and used for TA and FLTA functions (Jeppesen)
Displayed on map and used for TA and FLTA functions. The IFD is shipped from the factory with this database already loaded and updates are anticipated to be a rare occurrence.
Table 121 Database Update Cycle
In the event the terrain data ever needs updating, this is also performed through the front panel USB port.
Use one of the formatted fobs supplied by Avidyne (marked by the Avidyne logo printed on one side). In the event one of those fobs are not available, either call Avidyne for a replacement fob (a nominal fee will be charged) or purchase a replacement through other means. Acceptable alternative USB drives are FAT32 format, between 1-16 GB, and manufactured by WINTEC filemate. (http://www.wintecind.com/features/FileMate/USBFlashDrives.html).
To perform a data update, ensure the data to be updated is placed onto one of the acceptable USB fobs. Carefully insert the USB fob into the IFD USB slot while power is turned off. When the IFD is powered up, select the "Setup" tab of the SYS page and then pick the "Update Databases" LSK.
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Figure 31 Update Databases LSK
You will be prompted to "Confirm" or "Cancel". Assuming you selected "Confirm", you should see a dialog box presented in the middle of the screen and all uploadable files on that fob will be individually listed and check marks may be visible next to each file name.
Figure 32 Confirm and Cancel LSK
Use the "Select All", "Un-select All" LSKs and the IFD knob as required to ensure check marks are associated with all the desired files to upload to the IFD. Now press the "Proceed" LSK to begin the file upload.
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Figure 33 LSK Options
A progress bar will be presented to help provide an idea of how much longer the upload will take.
Figure 34 Progress Bar
Typical upload times are: · Worldwide Obstacles (1.5 MB) 5 sec · Eastern US Charts (100 MB) 3 min · US Charts (180 MB) 5 ½ min · Worldwide Charts (430 MB) 13 min · US Nav Data (8 MB) 3 ½ min · Europe Nav Data (10 MB) 2 ½ min · Australian Nav Data (1.5 MB) 30 sec · Worldwide Nav Data (15 MB) 7 Min
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For multiple IFD installations, the database uploads must be performed individually for each IFD to be updated. Due to some of the upload durations, Avidyne recommends creating a fob for each IFD to be updated so that the updates can happen in parallel and not stacked serially, thereby extending the overall time to accomplish a full update. A clear indication is presented when the data uploads have been completed. Likewise, if the USB fob was removed prior to finishing the data upload, an error message will be presented and the entire process will need to be manually restarted once the fob is reinserted in the IFD.
Figure 35 Update Complete Indication
When you are all done press the "Done" LSK, which will restart the IFD into flight mode. Remove the USB fob and perform a normal start up. It is highly recommended to verify the data was updated from the "Setup" LSK of the SYSTEM tab on the AUX page.
If an IFD is in normal operating mode (not maintenance mode), the presence of a USB fob is ignored and these pages cannot be accessed.
10.2 Datalogs Download
There is extensive data-logging that is automatically done on all IFDs. These datalogs can be accessed post-flight and used for a number of purposes.
There are five types of datalogs employed in the IFDs:
· System Log This log provides an in-depth record of the navigation state. From this log, you can re-create many aspects of the FMS output and IFD state. It logs at a rate of approximately 1Hz;
· Flight Log This log provides a detailed record of your aircraft state as measured by the various IFD sensors. It logs at a rate of approximately 5Hz;
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· Engine Log This log provides details on fuel flow sensor data (if configured). It logs at a rate of approximately ¼ Hz;
· Event Log This log contains miscellaneous data such as all alerts, keystrokes, system status and error messages, etc. It is designed to be diagnostics log for Avidyne Service Center technicians and not expected to be used by owners/operators. It logs at an on-condition rate;
· Voltage Log This log contains internal diagnostic data such as the voltages and currents on sub-system boards, temperatures and internal fan status. It logs at a rate of approximately 1Hz.
· Download Configuration Info - This log contains the system configuration for the unit.
· GPS Log - This log contains detailed internal state data for the GPS.
The "Download Logs" LSK is presented when "Software" is selected on the SYS tab and the system is not in-air. When the "Download Logs" LSK is pressed, a pair of Confirm/Cancel LSKs are presented. Selecting Confirm will launch the Maintenance Mode of the IFD5XX/4XX. From Maintenance Mode, press the right side of the AUX page function key to select the "Logs" tab. Ensure a USB fob is inserted in the IFD front bezel USB port and then use a combination of the left side LSKs and the bottom right IFD knob to select the desired combination of logs and type of action to perform.
Figure 36 Datalogs Download Page
Pressing the "Proceed" LSK will immediately start downloading all logs listed in the center of the page with green check marks adjacent to them. If only a subset of the logs are to be downloaded, use the "Un-Select All" LSK to deselect all logs and then use the bottom right IFD knob to highlight the desired log and push in to generated a green check mark.
The "Logs" LSK on that Maintenance Mode page provides two options for downloading this data via dedicated LSKs. The first option ("Full") allows a download of all data logs onto the USB fob. The second option ("Since Last") downloads the data logged since the last time a download was completed. Since the logs contain a large amount of data, the second option will be a quicker option in almost every case.
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Download times are highly dependent on the number and types of logs being downloaded and how it's been since the last download. Times can range from a few seconds to more than 15 minutes. The more often logs are downloaded, the shorter the download times will be.
In order to provide an indication of download progress, a progress bar will be presented with both a symbolic aircraft indicating download in progress and a % complete estimate. The files to be downloaded can have one of several states "OK", "In progress...", "Pending", "Skipped", "Active", "Failed".
When downloaded to the USB fob, the data logs will be saved in .csv files. This can be imported into newer versions of Microsoft Excel into a table format. The data can then be plotted or analyzed by several 3rd party tools. Note that files can easily contain 50MB or more of data.
10.3 Software Update
The following procedures should be followed when performing optional or mandatory software change to the IFD System:
1. Acquire the software image and associated loading procedure from the manufacturer.
2. Verify the software part number configuration before and after maintenance is performed on the airborne equipment using the loading procedure instructions.
3. It is the responsibility of maintenance personnel to ensure the identified part is recorded in the necessary maintenance logs.
4. It is the maintenance personnel's responsibility to ensure that the software part identification has been logged. When new software is loaded into the unit, the correct software part number should be verified according to the instructions accompanying the software change before the unit is returned to service. Hardware versions are identified on the data label by brackets following the main part number.
Changes to software part number, version, and/or operational characteristics should be reflected in the Operator's Manual, Aircraft Flight Manual, Aircraft Flight Manual Supplement, and/or any other appropriate document.
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11. Periodic Maintenance
The IFD5XX/4XX does not require any periodic or preventative maintenance. Maintenance on the IFD5XX/4XX is on condition.
11.1 Equipment Calibration
The IFD5XX/4XX has no required servicing tasks.
11.2 VOR Checks
Every 30 days, verify the limits of the VOR per 14 CFR §91.171. Only required for IFR operations. (N/A for IFD510/545/410)
11.3 Cleaning
The front display and bezel may require cleaning periodically, reference Section 13.
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12. Factory Service Policies and Procedures
12.1 Technical Support
Avidyne's website contains information that may assist the operator and installer with questions or problems with their Avidyne IFD5XX/4XX. Technical support questions may be submitted, via the following:
·
Email: techsupport@avidyne.com
·
Fax: 781-402-7599
·
Voice: 1-888-723-7592
·
Internet: www.Avidyne.com
An Avidyne Technical Support Representative will respond as soon as possible. Avidyne business hours are:
·
Monday through Friday: 8:00 AM to 5:00 PM Eastern Time
Please include the part number, revision number and serial number of the unit in all correspondences. For problem reporting, please provide as many details associated with the problem as possible.
For After Hours Technical Support, via the following:
·
AOG Support: 877-900-4AOG (4264)
12.2 General Service Procedures
Repair of the IFD5XX/4XX are performed at authorized Part 145 service centers and the Avidyne factory.
Prior to returning a unit for service, contact Avidyne at 1-888-723-7592 to obtain a Return Merchandise Authorization (RMA) number.
When calling or emailing for product-related help, please have the following information available:
1. Customer Name/Account Information
2. IFD5XX/4XX Serial Numbers either read it from the label physically attached to back of IFD (need to partially remove the IFD to see it), or get it from the aircraft maintenance records.
3. IFD5XX/4XX Software Part Numbers: Press the "SYS" page function key and then tab over to the "Setup" tab. Record the "Software Version" and the "Flight Software Part Number". Also make a note of any other yellow text on that page.
4. Be prepared to download the aircraft flight logs and email/transmit them to Avidyne Customer Service.
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13. Bezel and Display Cleaning
If the IFD screen should become dirty due to fingerprints or dust, clean the screen using the following materials and methods: A clean, soft lint-free cloth such as 3M Ultra-Brite Cloth #2011 or similar; A cleaning solution composed of a 1:1 ratio of de-ionized water and isopropyl alcohol (IPA). Use caution, as it may be flammable. Always apply the cleaning solution directly on the cloth. Never spray cleaner directly on the screen. In general, isopropyl alcohol is a safe and effective cleaner. Methanol and most acidic solutions can be toxic or damaging to glass coatings if misused. Excessive or unnecessary cleaning should be avoided to prevent damage to the coated optical filter surfaces. Never allow excess amounts of cleaning agents to dry if they have formed into pools, streaks or droplets to help avoid spotting of the glass surface. The use of any 3rd party screen protector, especially those that adhere directly to the IFD display glass, is not endorsed by Avidyne due to the touch-screen nature of the display and may void the warranty for any display related issue.
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Appendix A: Environmental Qualification Form
IFD540, IFD510, IFD440, IFD410
Environmental Tests
RTCA/DO160G Section
Test Category
Temperature and Altitude
4.0
Low Temp
4.5.2
Equipment qualified to Category C1
High Temp
4.5.3 & 4.5.4 Equipment qualified to Category C1
In-Flight Loss of Cooling
4.5.5
Equipment qualified to Category W
Altitude
4.6.1
Equipment qualified to Category C1
Decompression
4.6.2
Equipment qualified to +55,000 Ft.
Overpressure
4.6.3
Equipment qualified to -15,000 Ft.
Temperature Variation
5
Equipment qualified to Category B
Humidity
6
Equipment qualified to Category A
Operational Shocks & Crash Safety
7
Equipment qualified to Category E
Vibration
Equipment qualified to Category S,
8
Curves B and M, Category U, Curve G
Explosive Atmosphere
9
Category X, no test performed
Waterproofness Fluids Susceptibility
10
Category X, no test performed
11
Category X, no test performed
Sand and Dust
12
Category X, no test performed
Fungus Resistance
13
Category X, no test performed
Salt Spray Magnetic Effects Power Input
14
Category X, no test performed
15
Equipment qualified to Class Z
16
Equipment qualified to Category B
Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility
Radio Frequency Susceptibility Emission of Radio Frequency Energy
Lightning Induced Transient Susceptibility
17
Equipment qualified to Category A
18
Equipment qualified to Category B
19
Equipment qualified to Category ZC
Equipment qualified to Category W
20
(conducted)/WR (radiated)
21
Equipment qualified to Category M
Category B4HZL4 (Power) and B3K4L4
22
(All other I/O)
Lightning Direct Effects
23
Category X, no test performed
Icing
24
Category X, no test performed
Electrostatic Discharge
25
Equipment qualified to Category A
Fire and Flammability
26
Category X, no test performed
Avidyne recommends the following for helicopter installations:
Plug & Play VFR Installations Installer has option to use existing tray;
New VFR Installations Installer should use Avidyne's Helicopter Tray, reference Table 26 or Table 27;
All IFR Installations Installer must use Avidyne's Helicopter Tray, reference Table 26 or Table 27.
Table 122 Environmental Qualification Form - IFD540/510/440/410
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IFD550, IFD545
(Low Temp and Vibration Categories Differ From Table 122)
Environmental Tests
RTCA/DO160G Section
Test Category
Temperature and Altitude
4.0
Equipment qualified to Category X
(non-standard category)
Low Temp
4.5.2
Equipment tested to C1 with Ground Survival Low limited to -40C
High Temp
4.5.3 & 4.5.4 Equipment qualified to Category C1
In-Flight Loss of Cooling
4.5.5
Equipment qualified to Category W
Altitude
4.6.1
Equipment qualified to Category C1
Decompression
4.6.2
Equipment qualified to +55,000 Ft.
Overpressure
4.6.3
Equipment qualified to -15,000 Ft.
Temperature Variation
5
Equipment qualified to Category B
Humidity
6
Equipment qualified to Category A
Operational Shocks & Crash Safety
7
Equipment qualified to Category E
Vibration
Equipment qualified to Category S,
8
Curves B and M
Explosive Atmosphere
9
Category X, no test performed
Waterproofness Fluids Susceptibility
10
Category X, no test performed
11
Category X, no test performed
Sand and Dust Fungus Resistance Salt Spray Magnetic Effects Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility
Radio Frequency Susceptibility Emission of Radio Frequency Energy
Lightning Induced Transient Susceptibility Lightning Direct Effects Icing Electrostatic Discharge Fire and Flammability
12
Category X, no test performed
13
Category X, no test performed
14
Category X, no test performed
15
Equipment qualified to Class Z
16
Equipment qualified to Category B
17
Equipment qualified to Category A
18
Equipment qualified to Category B
19
Equipment qualified to Category ZC
Equipment qualified to Category W
20
(conducted)/WR (radiated)
21
Equipment qualified to Category M
Category B4HZL4 (Power) and B3K4L4
22
(All other I/O)
23
Category X, no test performed
24
Category X, no test performed
25
Equipment qualified to Category A
26
Category X, no test performed
Table 123 Environmental Qualification Form - IFD550/545
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Appendix B: STC Permission
Avidyne Corporation hereby grants to all National Aviation Authorities (FAA, CAA, JAA, etc) approved installers the use of data from STC SA00343BO to install the Avidyne IFD5XX/4XX System. This also includes any international validations of the STC (e.g. EASA, ANAC, etc). Copies of the STC data are available on the Avidyne website Technical Publications page or upon request. The latest data revisions are listed in Avidyne 700-00182XXX/700-00179-XXX Master Document List, AVIFD-306.
Installers must abide by the conditions and limitations stated in both the STC and in the Installation Manual in order to maintain compliance. The use of this data by itself does not constitute installation approval.
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Appendix C: Mechanical Drawings
Figure C - 1 IFD5XX Tray Installation .............................................................................................. 154 Figure C - 2 IFD4XX Tray Installation .............................................................................................. 155 Figure C - 3 IFD5XX Instrument Panel Cutout ................................................................................ 156 Figure C - 4 IFD4XX Instrument Panel Cutout ................................................................................ 157 Figure C - 5 Typical GPS Antenna Installation ................................................................................ 158 Figure C - 6 AT-575 GPS Antenna Hole Pattern .............................................................................. 158 Figure C - 7 AV-801 GPS Antenna Hole Pattern ............................................................................. 159 Figure C - 8 Typical GPS Antenna Doubler Installation ................................................................. 160 Figure C - 9 Typical GPS Antenna Doubler .................................................................................... 161
Figure C - 1 IFD5XX Tray Installation
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Figure C - 2 IFD4XX Tray Installation
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Figure C - 3 IFD5XX Instrument Panel Cutout
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Figure C - 4 IFD4XX Instrument Panel Cutout
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Figure C - 5 Typical GPS Antenna Installation
Forward
Figure C - 6 AT-575 GPS Antenna Hole Pattern
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Figure C - 7 AV-801 GPS Antenna Hole Pattern
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Figure C - 8 Typical GPS Antenna Doubler Installation
Fuselage Skin Thickness 0.016" - 0.025"
0.016" - 0.025"
Adjacent Structure Rivet Type
Dimpled skin / Countersunk Rivets
Protruding Head Rivets
Doubler Thickness 0.020"
0.020"
Outer Rivet Row in Doubler
MS20426AD3 (Double Dimple)
MS20470AD3
0.032" - 0.050" 0.032" - 0.050"
Countersunk Skin / Countersunk Rivets
Protruding Head Rivets
0.032" 0.032"
NAS1097AD4 (Countersunk)
MS20470AD4
Table 124 Rivet/ Doubler Selection
Rivet type is dependent on the type of rivets in the adjacent fuselage structure. If the adjacent rivets in the structure around the bay selected for the doubler installation are protruding head type, install MS20470AD rivets in the outer row of the doubler. If the adjacent rivets are countersunk or dimpled, install either MS20426AD or NAS1097AD rivets per the table above.
Inner Four Rivet in Doubler
MS20426AD3 (Double Dimple)
MS20426AD3 (Double Dimple)
NAS1097AD4 (Countersunk)
NAS1097AD4 (Countersunk)
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Figure C - 9 Typical GPS Antenna Doubler
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Appendix D: Electrical Interface Drawings
Figure D - 1: Lighting, Power, and Antenna Interconnect .................................................................... 164 Figure D - 2: Blind Altitude Encoders Interconnect .............................................................................. 167 Figure D - 3: RS-232 Serial Data Interconnect ..................................................................................... 168 Figure D - 4: EFIS Interconnect ........................................................................................................... 170 Figure D - 5: Generic EFIS Interconnect............................................................................................... 171 Figure D - 6: Proline 21 EFIS & APS 3000 AP .................................................................................... 172 Figure D - 7: Proline 21 EFIS & APS 3000 AP ................................................................................ 173 Figure D - 8: Proline 21 EFIS & APS 3000 AP .................................................................................... 174 Figure D - 9: Proline 21 EFIS & APS 3000 AP .................................................................................... 175 Figure D - 10: Proline 21 EFIS & APS 3000 AP .................................................................................. 176 Figure D - 11: EHSI ARINC 429 Interconnect, Dual IFD5XX/4XX, Sandel SN3308 Interconnect ...... 177 Figure D - 12: ARINC 429/RS-232 Air Data/IRU/AHRS Interconnect ................................................ 179 Figure D - 13: Sandel SN3500 Interconnect ......................................................................................... 181 Figure D - 14: Traffic Advisory Interconnect ........................................................................................ 182 Figure D - 15: GTX 330 Interconnect ................................................................................................... 184 Figure D - 16: Terrain and Weather Interconnect ................................................................................. 185 Figure D - 17: Weather Interconnect..................................................................................................... 186 Figure D - 18: Audio Panel Interconnect .............................................................................................. 187 Figure D - 19: VOR/ILS Indicator Interconnect.................................................................................... 189 Figure D - 20: Main Indicator Interconnect .......................................................................................... 190 Figure D - 21: Main Indicator KI209 Interconnect................................................................................ 191 Figure D - 22: Main Indicator KI208 Interconnect................................................................................ 192 Figure D - 23: Main Indicator MD200-20X/-30X Interconnect ........................................................... 193 Figure D - 24: RMI/OBI Interconnect .................................................................................................. 194 Figure D - 25: King Serial DME Tuning Interconnect, Panel Mount.................................................... 195 Figure D - 26: King Serial DME Tuning Interconnect, Remote Mount................................................. 196 Figure D - 27: Parallel DME Tuning Interconnect ............................................................................... 197 Figure D - 28: Parallel DME Tuning Interconnect ............................................................................... 198 Figure D - 29: TAWS Interconnect....................................................................................................... 199 Figure D - 30: Autopilot Interconnect................................................................................................... 200 Figure D - 31: Bendix/King Autopilot Interconnect .............................................................................. 201 Figure D - 32: Century Autopilot Interconnect..................................................................................... 202 Figure D - 33: S-Tec Autopilot Interconnect ......................................................................................... 204
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Figure D - 34: Collins Autopilot Interconnect....................................................................................... 206 Figure D - 35: Bendix King KFC400 Autopilot Interconnect................................................................. 207 Figure D - 36: External Navigation Source and GPS Annunciators Interconnect.................................. 208 Figure D - 37: Switch Interconnect....................................................................................................... 210 Figure D - 38: Garmin GAD 42 Interconnect ....................................................................................... 211 Figure D - 39: Garmin G600 Interconnect ............................................................................................ 212 Figure D - 40: Avidyne Entegra Interconnect ....................................................................................... 213 Figure D - 41: Avidyne EX500/600/5000 Interconnect ......................................................................... 214 Figure D - 42: Aspen EFD1000 Interconnect (without ACU) ............................................................... 215 Figure D - 43: Aspen EFD1000 Interconnect (with ACU) .................................................................... 216 Figure D - 44: Transponder Interconnect.............................................................................................. 217 Figure D - 45: ELT Interconnect........................................................................................................... 218 Figure D - 46: Skytrax100B (formerly MLB100) ADS-B IN Receiver Interconnect ............................... 219 Figure D - 47: RDR2000 Interconnect.................................................................................................. 220 Figure D - 48: GTX 335 Interconnect ................................................................................................... 221 Figure D - 49: GTX 345 Interconnect ................................................................................................... 222 Figure D - 50: GTX 330ES Interconnect............................................................................................... 224 Figure D - 51: Avidyne AXP322 Interconnect ...................................................................................... 225 Figure D - 52: Avidyne Dual AXP322 Interconnect ............................................................................. 226 Figure D - 53: FreeFlight FDL 978RX Interconnect ........................................................................ 227 Figure D - 54: GDL 88 Interconnect ................................................................................................. 229 Figure D - 55: Avidyne AXP340 Interconnect .................................................................................. 230 Figure D - 56: XMD076 Interconnect................................................................................................ 231 Figure D - 57: Single GDU700/1060 PFD Interconnect .................................................................. 232 Figure D - 58: Dual GDU700/1060 PFD Interconnect..................................................................... 233 Figure D - 59: Garmin G5 EHSI Interconnect .................................................................................. 234 Figure D - 60: Garmin G5 EADI Interconnect .................................................................................. 235 Figure D - 61: Garmin G5 EFIS Interconnect .................................................................................. 236 Figure D - 62: NGT9000R Interconnect ........................................................................................... 237 Figure D - 63: KT-74 Interconnect .................................................................................................... 238 Figure D - 64: TDR-94 Interconnect ................................................................................................. 239
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AVIDYNE IFD5XX/
4XX
P1001
AIRCRAFT POWER 1 19
AIRCRAFT POWER 1 20
22 AWG 22 AWG
AIRCRAFT POWER 2 72 AIRCRAFT POWER 2 15
22 AWG 22 AWG
AIRCRAFT GROUND 77 AIRCRAFT GROUND 78
22 AWG 22 AWG
LIGHTING BUS HI 39 LIGHTING BUS LO 40
22 AWG 22 AWG
P1002
AIRCRAFT POWER 11
20 AWG
12
AIRCRAFT POWER 12
20 AWG
AIRCRAFT GROUND 21
20 AWG
12
AIRCRAFT GROUND 22
20 AWG
P1006
AIRCRAFT POWER 44
22 AWG
12
AIRCRAFT GROUND 41
22 AWG
18 AWG
5A for 28VDC 7.5 for 14VDC
18 AWG
5A for 28VDC 7.5 for 14VDC
18 AWG
2 3 11
AIRCRAFT POWER
10 11
AIRCRAFT POWER
LIGHTING BUS HIGH
4
LIGHTING BUS LOW
18 AWG
2 3 5 12
10A
AIRCRAFT POWER
18 AWG 12
NAV FLAG CIRCUIT BREAKER
2A
2 3 6 12
AIRCRAFT POWER
P1003 7
GPS ANTENNA
GPS ANTENNA
P1004
12
COM ANTENNA
COM ANTENNA
12
P1005
12
VOR/LOC ANTENNA
P1007
VOR
12 GLIDESLOPE ANTENNA
G/S
S
NAV ANTENNA
12
DIPLEXER
9 12
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Figure D - 1: Lighting, Power, and Antenna Interconnect
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IFD5XX/4XX #1 P1003
GPS ANTENNA
P1004
12
COM ANTENNA
P1005
12
VOR/LOC ANTENNA
P1007
12 GLIDESLOPE ANTENNA
IFD5XX/4XX #2 P1007
12 GLIDESLOPE ANTENNA
P1005
12
VOR/LOC ANTENNA
P1003
GPS ANTENNA
P1004
12
COM ANTENNA
7
GPS ANTENNA 1
COM ANTENNA 1 12
8
G/S 1
VOR 1
DIPLEXER S
G/S 2 12 VOR 2
NAV ANTENNA 12
7
GPS ANTENNA 2
COM ANTENNA 2 12
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NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. IF AIRCRAFT HAS MULTIPLE POWER BUSSES, IT IS RECOMENDED THAT IFD54XX/4XX POWER CONNECTIONS BE CONNECTED AS DESCRIBED IN SECTION 4.
3. AIRCRAFT POWER INPUT TO THE IFD5XX/4XX MAY BE 9-33 VDC.
4. THE IFD5XX/4XX SHOULD BE CONFIGURED FOR THE CORRECT LIGHTING BUS VOLTAGE POST-INSTALLATION. NO DAMAGE WILL OCCUR IF THE UNIT IS CONFIGURED INCORRECTLY. IN ADDITION, LIGHTING CAN BE SET TO AUTOMATICALLY COMPENSATE FOR AMBIENT LIGHTING CONDITIONS USING ITS LIGHT SENSOR. A MANUAL LIGHTING CONTROL OPTION IS ALSO AVAIABLE. REFER TO THE POST-INSTALLATION CONFIGURATION PROCEDURE.
5. MAXIMUM ALLOWABLE WIRE GAUGE INTO P1002 PINS IS 20 AWG.
6. THE AIRCRAFT POWER INPUT P1006-44 PROVIDES POWER FOR THE VOR/LOC SUPERFLAG (P1006-15) AND GLIDESLOPE SUPERFLAG (P1006-38) OUTPUTS. NO POWER CONNECTION IS REQUIRED ON P1006-44 IF THESE FLAG OUTPUTS ARE NOT USED.
7. THE GPS ANTENNA COAXIAL CABLE MUST BE DOUBLE OR TRIPLE SHIELDED AND THE LOSS (INCLUDING CONNECTORS) MUST BE GREATER THAN 1.5 dB AND LESS THAN 6.5 dB.
8. COMMANT CI1125 DIPLEXER, OR EQUIVALENT, SHOULD BE USED.
9. COMMANT CI507 DIPLEXER, OR EQUIVALENT, SHOULD BE USED.
10. ACFT PWR 1 IS INTERNALLY DIODE ISOLATED FROM ACFT PWR 2. ONLY ONE POWER INPUT IS REQUIRED FOR NORMAL OPERATION.
11. FOR THE MAIN POWER INPUT, A 14VDC INSTALLATION REQUIRES TWO AIRCRAFT POWER INPUTS AND TWO AIRCRAFT GROUND CONNECTIONS BE USED FOR EACH MAIN POWER INPUT USED. A 28VDC INSTALLATION REQUIRES A MINIMUM OF ONE POWER AND GROUND CONNECTION, BUT TWO ARE RECOMMENDED.
12. NOT APPLICABLE FOR IFD510/545/410
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IFD5XX/4XX
ALTITUDE D4 ALTITUDE A1 ALTITUDE A2 ALTITUDE A4 ALTITUDE B1 ALTITUDE B2 ALTITUDE B4 ALTITUDE C1 ALTITUDE C2 ALTITUDE C4 ALTITUDE COMMON
P1001
70 69 68 67 66 65 64 63 62 61 60
ACK Technologies
A-30
DB15
1 2 3 4 5 9 10 11 13 12 6
Trans -Cal
SSD-120 IA-RS232C-D
DB15 DB15 (MALE)
1
1
2
2
3
3
4
4
5
5
9
9
10
10
11
11
13
13
12
12
6
6
Sandia
SAE 5-35
J4
1 2 3 4 5 9 10 11 13 12 6
Bendix/King
KEA 130A KEA 346
P1
P1
1
A
2
B
3
C
4
M
5
N
9
P
10
D
11
L
13
U
12
V
6
R
Terra
AT 3000
P1
2 3 4 5 9 10 11 13 12 6
Encoding Altimeter Or Blind Encoder
D4 A1 A2 A4 B1 B2 B4 C1 C2 C4 COMMON
3
3
3
3
NOTES:
1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION.
3. THIS ENCODER MAY ALSO BE CONNECTED VIA RS-232.
Figure D - 2: Blind Altitude Encoders Interconnect
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IFD 5XX/4XX P1001
GPS RS-232 IN 2 59
GPS RS-232 OUT 1 56
GPS RS-232 IN 1 57 GPS RS-232 OUT 3 41
GPS RS-232 IN 3 42
GPS RS-232 OUT 4 54 GPS RS-232 IN 4 55
ACK Technologies A-30 DB15
7 (14) SHELL
-
-
Trans-Cal
Shodin
Icarus
SSD-120 8800T/9000T/9200T
3000
DB9
DB15
P3 (DB9)
4 (9) 5
7
2
15
SHELL
1
-
-
2
-
-
7
-
-
8
-
-
Sandia SAE 5-35
J4
1 (2) 5
Altitude Serializer/Encoder
RS-232 OUT HI RS-232 OUT LO
-
} CONFIG JUMPER (RESOLUTION)
-
} CONFIG JUMPER (OUTPUT FORMAT)
9
8
Garmin
Eventide
MX20/
Argus 3000/
GTX 327
GMX 200
5000/7000
37-PIN P3271
1P1
4
2
16
23
13
4
JP Instruments
FS 450
P1 9 SHELL
EDM-760
15-PIN F.F. 2
SHELL
Miniflo-L
Miniflo-L
EDM-700
91204XT(38)D 91204XT-D
2
9
9
SHELL
2
2
Shadin
Digiflo-L 91053XP
Digiflo-L 91053XT-D
Digidata 91802-( )
12
H
12
2
D
2
F/ADC-200 F/ADC-2000
J2 5 9
Insight
G3 P2 3 2
Electronics International
FP-55L
16 SHELL
RS-232 Receiver
RS-232 IN HI RS-232 IN LO
Garmin ARNAV
GTX 327
P3271 20 13
FC-10 FT-10 1P1
2 4
JP Instruments
FS 450
P1 6 SHELL
EDM-760
15-PIN F.F. 1
SHELL
EDM-700
1 SHELL
Miniflo-L 91204XT(38)D
6 2
Miniflo-L 91204XT-D
6 2
Shadin
Digiflo-L Digiflo-L Digidata 91053XP 91053XT-D 91802-( )
5
J
5
2
D
2
F/ADC-200 F/ADC-2000
J2 6 9
Electronics Insight
International
G3
FP-5L
P2
11
15
2
SHELL
Fuel/Air Data
RS-232 OUT HI RS-232 OUT LO
P1001
IFD540/440
42 GPS RS-232 IN 3 41 GPS RS-232 OUT 3
5
10 PX
PORTABLE RS-232 DEVICE
X
RS-232 IN
X
RS-232 OUT
Figure D - 3: RS-232 Serial Data Interconnect Page 1 of 2
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NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE.
3. REFER TO SECTION 7 FOR RS-232 CHANNEL SETTINGS
4. REFER TO THE GTX 327 TRANSPONDER INSTALLATION MANUAL, 190-00187-02, FOR COMPLETE INFORMATION.
5. IF TWO OR MORE IFD4XX/5XX SERIES UNITS ARE INSTALLED, THE RS-232 LINE ON P1001-41 AND P1001-42 MAY BE CROSS-CONNECTED TO CROSSFILL FLIGHT PLANS AND USER WAYPOINTS. TO CROSSFILL FLIGHT PLANS, IT IS REQUIRED THAT BOTH UNITS HAVE IDENTICAL DATABASE CYCLE DATES AND MAY BE REQUIRED THAT THEY HAVE IDENTICAL VERSIONS OF THE MAIN SOFTWARE. REFERENCE SECTION 4 FOR WIRING INFORMATION.
6. MAPMX (MAIN SOFTWARE VERSION 3.10 AND LATER) IS THE PREFERRED COMMUNICATION PROTOCOL FOR THE MX20/GMX200. OTHER INPUT PORTS ON MX20/GMX200 MAY BE USED INSTEAD OF THE PORT SHOWN. REFER TO APPROPRIATE MANUFACTURER'S INSTALLATION DOCUMENTATION.
7. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
88. IF USING THE SERIAL PORT SOFTWARE METHOD TO CONFIGURE THE OUTPUT OF THE ENCODER, ENSURE THAT THE "TRIMBLE/GARMIN 9600 BPS" FORMAT IS SELECTED.
99. MOD LEVEL 8 (OR HIGHER) IS REQUIRED TO SUPPORT RS-232 INTERFACE. ENSURE THAT JUMPERS ARE SET FOR "TRIMBLE/GARMIN 9600 BPS" AND "10 FOOT RESOLUTION."
10 THE IFD5XX/4XX STC DOES NOT PROVIDE INSTALLATION APPROVAL OF ANY PORTABLE ELECTRONIC DEVICES. ADDITIONAL INSTALLATION APPROVAL IS REQUIRED FOR THESE DEVICES.
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IFD 5XX/4XX #1 P1001
GPS ARINC 429 IN 1 A
48
GPS ARINC 429 IN 1 B
49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
P1006
6
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
IFD 5XX/4XX #2 P1001
GPS ARINC 429 IN 1 A
48
GPS ARINC 429 IN 1 B
49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
P1006
6
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
Collins EFIS-84 DPU-84
P1
4
142 138
122 126
125 129
Bendix/King EFS 40/50
SG 465
P4652A
P4652B
47 20
67 53
64 63
16 29
38 25
ARINC 429 EFIS DISPLAY #1
LNAV TRANSMITTER A LNAV TRANSMITTER B
LRN/LNAV 1 RECEIVER A LRN/LNAV 1 RECEIVER B
LRN/LNAV 2 RECEIVER A LRN/LNAV 2 RECEIVER B
NAV 1 RECEIVER A NAV 1 RECEIVER B
NAV 2 RECEIVER A NAV 2 RECEIVER B
Collins EFIS-84 DPU-84
P1
4
142 138 122 126
125 129
Bendix/King EFS 40/50
SG 465
P4652A
P4652B
47 20
67 53
64 63
16 29
38 25
ARINC 429 EFIS DISPLAY #2
LNAV TRANSMITTER A LNAV TRANSMITTER B
LRN/LNAV 1 RECEIVER A LRN/LNAV 1 RECEIVER B
LRN/LNAV 2 RECEIVER A LRN/LNAV 2 RECEIVER B
NAV 1 RECEIVER A NAV 1 RECEIVER B
NAV 2 RECEIVER A NAV 2 RECEIVER B
NOTES:
1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. IF THE GPS ARINC 429 IN 1 PORT (P1001-48 AND -49) IS ALREADY USED FOR ANOTHER PURPOSE, THE GPS ARINC 429 IN 2 PORT (P1001-50 AND -51) MAY BE CONNECTED INSTEAD.
4 THE DEPICTED COLLINS EFIS-84 INTERFACE DOES NOT SUPPORT SELECTION OF THE GPS COURSE VIA THE EFIS CONTROL PANEL, A GAD 42 IS REQUIRED FOR GPS SELECTED COURSE.
5. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
66. NOT APPLICABLE TO IFD 510/545/410
Figure D - 4: EFIS Interconnect
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IFD 5XX/4XX #1 P1001
4
GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B
48 49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
P1006
VOR/ILS ARINC 429 OUT A
24
5
VOR/ILS ARINC 429 OUT B
23
ARINC 429 EFIS DISPLAY #1
LNAV TRANSMITTER A LNAV TRANSMITTER B
LRN/LNAV 1 RECEIVER A LRN/LNAV 1 RECEIVER B
LRN/LNAV 2 RECEIVER A LRN/LNAV 2 RECEIVER B
NAV 1 RECEIVER A NAV 1 RECEIVER B
NAV 2 RECEIVER A NAV 2 RECEIVER B
IFD 5XX/4XX #2 P1001
GPS ARINC 429 IN 1 A
48
4 GPS ARINC 429 IN 1 B
49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
P1006
5
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
ARINC 429 EFIS DISPLAY #2
LNAV TRANSMITTER A LNAV TRANSMITTER B
LRN/LNAV 1 RECEIVER A LRN/LNAV 1 RECEIVER B
LRN/LNAV 2 RECEIVER A LRN/LNAV 2 RECEIVER B
NAV 1 RECEIVER A NAV 1 RECEIVER B
NAV 2 RECEIVER A NAV 2 RECEIVER B
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. IF RS-232 PORT 1 IS NOT AVAILABLE, USE ANY OTHER AVAILABLE PORT. 4 IF ARINC 429 PORT 1 IS NOT AVAILABLE, USE ANOTHER AVAILABLE PORT. 5 NOT APPLICABLE FOR IFD510/545/410
Figure D - 5: Generic EFIS Interconnect
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IFD5XX-1
P1006
VOR/ILS 429 OUT A 24 VOR/ILS 429 OUT B 23
IFD5XX-2
P1006 VOR/ILS 429 OUT A 24 VOR/ILS 429 OUT B 23
ICC-P1 (IAPS)
63 L-SRN-1 429 A 64 L-SRN-1 429 B
ICC-P101 (IAPS)
63 R-SRN-1 429 A 64 R-SRN-1 429 B
2PFD-P2 (COPILOT PFD)
17 R-SRN-2 429 A
2
18 R-SRN-2 429 B
MFD-P1
54 L-SRN-2 429 B 37 L-SRN-2 429 A
PFD-P1(PILOT PFD)
37 L-SRN-2 429 A 54 L-SRN-2 429 B
NOTES: 1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED. 2 IF INSTALLED 4. ON IFD-1 VOR/LOC/GS ARINC 429 CONFIG PAGE, SET SPEED TO LOW FOR RX AND TX, FORMAT TO VHF/GPS 429, SDI TO
VOR/ILS1 AND DME MODE TO DIRECTED FREQ 1 5. ON IFD-2, VOR/LOC/GS ARINC 429 CONFIG PAGE, SET SPEED TO LOW FOR RX AND TX, FORMAT TO (VHF/GPS 429 IF
CONFIGURING FOR LPV SUPPORT, OTHERWISE SET TO VHF 429), SDI TO VOR/ILS2 AND DME MODE TO DIRECTED FREQ 2 6. ADDITIONAL REMOTE ANNUNCIATIONS ARE REQUIRED FOR IFD-2 IF CONFIGURED FOR VHF/GPS 429 (LPV). REFER TO
SECTION 5 FOR ANNUNCIATOR REQUIREMENTS 7. REFER TO PROLINE 21 CONFIGURATION STRAPPING INSTRUCTIONS FOR MARKER BEACON CHANGES.
Figure D - 6: Proline 21 EFIS & APS 3000 AP
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IFD 1 WIRED AS FMS 2 INTERFACE OPTION - EXISTING FMS RETAINED
IFD4XX/5XX-1
P1001 GPS 429 OUT 1A 46 GPS 429 OUT 1B 47
2PFD-P2 (COPILOT PFD)
14 R-NMC-1 429 A 15 R-NMC-1 429 B
MFD-P2
15 R-NMC-1 429 B 14 R-NMC-1 429 A
1PFD-P2 (PILOT PFD)
14 R-NMC-1 429 A
3
15 R-NMC-1 429 B
ICC-P101(IAPS)
47 R-NMC-1 429 A 48 R-NMC-1 429 B
NOTES: 1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. IN MAINTENANCE MODE, MAIN ARINC 429 CONFIGURATION PAGE, SET OUT TO GAMA 429 PROLINE 21, LOW SPEED, SDI
TO LNAV2, AND VNAV TO DISABLE LABELS. 3 IF INSTALLED. 4. PROLINE 21 CONFIGURATION STRAPPING FOR IFD 1 AS FMS 2 MOD:
600-00299-000
Figure D - 7: Proline 21 EFIS & APS 3000 AP Page 2 of 5
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IFD 1 WIRED AS FMS 1 INTERFACE OPTION - EXISTING FMS REPLACED BY IFD1
IFD4XX/5XX-1
P1001 GPS 429 OUT 1A 46 GPS 429 OUT 1B 47
2PFD-P1 (COPILOT PFD)
35 L-NMC-1 429 A
3
36 L-NMC-1 429 B
MFD-P1
36 L-NMC-1 429 B 35 L-NMC-1 429 A
1PFD-P1 (PILOT PFD)
35 L-NMC-1 429 A 36 L-NMC-1 429 B
ICC-P1(IAPS)
47 L-NMC-1 429 A 48 L-NMC-1 429 B
600-00299-000
NOTES: 1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. IN MAINTENANCE MODE, MAIN ARINC 429 CONFIGURATION PAGE, SET OUT TO GAMA 429
PROLINE 21, LOW SPEED, SDI TO LNAV1, AND VNAV SET TO DISABLE LABELS. 3 IF INSTALLED.
Figure D - 8: Proline 21 EFIS & APS 3000 AP Page 3 of 5
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IFD5XX/4XX Installation Manual
IFD 2 WIRED AS FMS 2 INTERFACE OPTION - EXISTING FMS REPLACED BY IFD1
IFD4XX/5XX-2
P1001 GPS 429 OUT 1A 46 GPS 429 OUT 1B 47
2PFD-P2 (COPILOT PFD)
14 R-NMC-1 429 A
3
15 R-NMC-1 429 B
MFD-P2
15 R-NMC-1 429 B 14 R-NMC-1 429 A
1PFD-P2 (PILOT PFD)
14 R-NMC-1 429 A 15 R-NMC-1 429 B
ICC-P101(IAPS)
47 R-NMC-1 429 A 48 R-NMC-1 429 B
NOTES:
1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. IN MAINTENANCE MODE, MAIN ARINC 429 CONFIGURATION PAGE, SET OUT TO GAMA 429 PROLINE 21, LOW SPEED, SDI SET TO LNAV2, AND VNAV SET TO DISABLE LABELS.
3 IF INSTALLED
4. PROLINE 21 CONFIGURATION STRAPPING FOR MOD:
600-00299-000
Figure D - 9: Proline 21 EFIS & APS 3000 AP Page 4 of 5
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IFD5XX-2
P1001 GPS 429 IN 1B 49 GPS 429 IN 1A 48
23
IFD5XX-1
P1001
GPS 429 IN 1A 48 GPS 429 IN 1B 49
ICC-P101(IAPS)
1 R-GP-5 429 A 2 R-GP-5 429 B
23
EXISTING FMS (OPTIONAL)
D8 429B IN C8 429A IN
NOTES: 1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED. 2 FOR EACH IFD CONFIGURE THE IFD MAIN ARINC 429 INPUT SPEED TO HIGH, AND DATA TO EFIS/AIRDATA. 3 FOR EACH IFD SELECT THE IFD MAIN SYSTEM CONFIG. PAGE AND SET JOYSTICK INPUT TO DISABLED.
Figure D - 10: Proline 21 EFIS & APS 3000 AP Page 5 of 5
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IFD5XX/4XX Installation Manual
IFD 5XX/4XX #1
P1006
VOR/ILS ARINC 429 OUT A
24
12
VOR/ILS ARINC 429 OUT B
23
P1001
GPS ARINC 429 IN 1 A
48
GPS ARINC 429 IN 1 B
49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
ILS/GPS APPROACH
14
MAIN +TO
25
MAIN +FROM
26
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
MAIN +UP
27
MAIN +DOWN
28
MAIN VERTICAL +FLAG
29
MAIN VERTICAL -FLAG
30
12
IFD 5XX/4XX #2
P1006
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
P1001
GPS ARINC 429 IN 1 A
48
GPS ARINC 429 IN 1 B
49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
MAIN +TO
25
MAIN +FROM
26
ILS/GPS APPROACH
14
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
MAIN +UP
27
MAIN +DOWN
28
MAIN VERTICAL +FLAG
29
MAIN VERTICAL -FLAG
30
9 NAV SYSTEM 1
(RELAXED) N/C
(ENERGIZED) NAV SYSTEM 2 AIRCRAFT POWER
N/C 10
VOR/ILS 1 (RELAXED)
VOR/ILS 2 (ENERGIZED) AIRCRAFT POWER
Sandel SN3308
P1
P2
P3
33
9
27
5
21 11 29
10 28
27 26 7
3
12
17 35
37 19
18 36
16 34
15 33
8
ARINC 429 EHSI DISPLAY #1 4
NAV ½ RELAY SENSE 5
429-2 RX-A 429-2 RX-B
VHF NAV 2 SWITCHING RELAY
GPS 2 SWITCHING RELAY 429-1 TX-A 429-1 TX-B
429-1 RX-A 429-1 RX-B
ILS 1 ENERGIZE 429-3 RX-A 429-3 RX-B
CDI SOURCE CONTROL 5
RCVR ½
5
+TO (FLAG) +FROM (FLAG)
CDI+ L CDI+ R
NAV+ VALID (FLAG) NAV- VALID (FLAG)
GSI+ UP GSI+ DOWN
GS+ VALID (FLAG) GS- VALID (FLAG)
ILS 2 ENERGIZE
8
6
Autopilot
LOCALIZER ENGAGE +LEFT +RIGHT LATERAL +FLAG LATERAL -FLAG +UP +DOWN VERTICAL +FLAG VERTICAL -FLAG
Figure D - 11: EHSI ARINC 429 Interconnect, Dual IFD5XX/4XX, Sandel SN3308 Interconnect Page 1 of 2
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NOTES:
1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE.
3. IFD540/440 #1 SETUP MAIN ARINC 429 CONFIG:
IN 1: LOW, SANDEL EHSI OUT: LOW, GAMA 429 GRPH W/INT SDI: LNAV 1 VNAV: DISABLE LABELS
VOR/LOC/GS ARINC 429:
SDI: VOR/ILS 1
SPEED:
RX:
TX:
LOW SPEED LOW SPEED
IFD540/440 #2 SETUP MAIN ARINC 429 CONFIG:
IN 1: LOW, SANDEL EHSI OUT: LOW, GAMA 429 GRPH W/INT SDI: LNAV 2 VNAV: DISABLE LABELS
VOR/LOC/GS ARINC 429:
SDI: VOR/ILS 2
SPEED:
RX:
TX:
LOW SPEED LOW SPEED
4. SANDEL SN3308 #1 AND #2 SETUP ITEMS:
LNAV 1/2 SELECT: IFD540
NAV CHANGE:
NAV-1 ENABLE: YES
PORT:
429 PORT-2*
NAV-2 ENABLE: YES
PORT:
429 PORT-2*
ANNUN: COURSE: DEVIATION: OBS ROT: OBS CAL:
SERIAL OBS/LEG ANALOG/IN NORMAL 000.0
RELAY SENSE:
NAV-2:
P2-33
GPS-1:
OFF
GPS-2:
OFF
CDI SRC SEL: P2-3
RCVR 1/2: P2-12
*NAV 1 /2 MUST TEMPORARILY BE SET TO "ANALOG" AND ILS MUST BE SET TO "VALID LOW" FOR PROPER OPERATION OF THE VDI.
5. THESE PINS ON THE SANDEL SN3308 ARE CONFIGURABLE AND CAN BE CHANGED TO SUIT THE PARTICULAR INSTALLATION.
6. AUTOPILOT SHOWN FOR REFERENCE ONLY. REFER TO APPROPRIATE AUTOPILOT INTERCONNECT DIGRAM.
7. IF IT IS DESIRED TO USE THE NAV RECEIVERS AS A SOURCE FOR THE SN3308 BEARING POINTERS, IT IS RECOMMENDED THAT THE IFD540/440 #1/#2 COMPOSITE OUTPUTS (P1006-8) BE CONNECTED TO THE SN3308 COMPOSITE INPUTS (P1-29 AND P1-10, #1 AND 2# RESPECTIVELY) AND THE SN3308 BRG NAV-1/NAV-2 BE SET TO "429+COMP".
88. ANALOG CONNECTIONS TO THE SN3308 ARE REQUIRED TO ALLOW VERTICAL GUIDANCE TO BE DISPLAYED FOR GPS APPROACHES.
9. USE RELAY AMERI-KING P/N AK-950-R12-()V OR EQUIVALENT.
1100 . USE RELAY LEACH P/N WN460-() () () OR EQUIVALENT.
11. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION.
12 NOT APPLICABLE FOR IFD510/545/410
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
3 GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B
48 49
Shadin
ADC 2000
J2 (DB15)
7 8
J1 (MS CONN)
40 22
2600
6 8
B&D
2601 2800 90004-003
P201
14
11
27
13
28
9
Bendix/King
KDC 281 KDC 481
P2811
5 6
P4811
U i
AIR DATA COMPUTER
TRANSMITTER A TRANSMITTER B
IFD5XX/4XX
P1001
3 GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B
48 49
Bendix/King
KAU 461
P1B 26 27
Collins
AHC-85E
P1 16 14
Honeywell Laseref
HG 1075AB HG 1095AB INSERT B
G7 G8
Litef
LTR-81
INSERT B G7 G8
Litton
LTN 90-100 LTN 91
INSERT B G7 G8
LTN 92
J1B 49 50
IRU/AHRS
IRU/AHRS TRANSMITTER A IRU/AHRS TRANSMITTER B
IFD5XX/4XX
P1001
GPS RS-232 OUT 1
56
GPS RS-232 IN 1
57
Insight TAS 1000 DSUB-25 PLUG
23 10
Sandia SAC 7-35
J100 25 13
AIR DATA COMPUTER
RS-232 RXD RS-232 TXD
Figure D - 12: ARINC 429/RS-232 Air Data/IRU/AHRS Interconnect Page 1 of 2
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IFD5XX/4XX Installation Manual
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE. THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL. 3. IF THE GPS ARINC 429 IN 1 PORT (P1001-48 AND -49) IS ALREADY USED FOR ANOTHER PURPOSE, THE GPS ARINC 429 IN 2 PORT (P1001-50 AND -51) MAY BE CONNECTED INSTEAD. 4. REFER TO SECTION 7 FOR ARINC 429 CHANNEL SETTINGS. 5. REFER TO SECTION 7 FOR RS-232 CHANNEL SETTINGS. 6. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPELTE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
GPS ARINC 429 OUT A 46 GPS ARINC 429 OUT B 47
GPS ARINC 429 IN 1A 48 GPS ARINC 429 IN 1B 49
P1006
VOR/ILS 429 OUT A 24
4
VOR/ILS 429 OUT B 23
P2
SANDEL SN3500 3
31/(2) GPS ARINC 429 IN A 17/(32) GPS ARINC 429 IN B
30 GPS ARINC 429 OUT A 15 GPS ARINC 429 OUT B
3/(35) NAV ARINC 429 IN A 33/(21) NAV ARINC 429 IN B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT INFORMATION AND CONFIGURATION.
4
NOT APPLICABLE FOR IFD510/545/410
Figure D - 13: Sandel SN3500 Interconnect
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IFD5XX/4XX Installation Manual
9
IFD5XX/4XX
P1001
GPS ARINC 429 IN 1 A
48
2 GPS ARINC 429 IN 1 B
49
ANNUNCIATE D
10
ANNUNCIATE E
11
IFD5XX/4XX
7
9 P1001
GPS ARINC 429 IN 1 A
48
2 GPS ARINC 429 IN 1 B
49
ANNUNCIATE D
10
ANNUNCIATE E
11
IFD5XX/4XX
GPS ARINC 429 IN 1 A
2 GPS ARINC 429 IN 1 B
9
P1001
48 49
ANNUNCIATE D
10
ANNUNCIATE E
11
IFD5XX/4XX
13
GPS RS-232 OUT 2
9 P1001
58
GPS RS-232 IN 2
59
IFD5XX/4XX
P1001
GPS ARINC 429 IN 2A
50
GPS ARINC 429 IN 2B
51
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
3
3
OPTIONAL REMOTE MUTE SWITCH
TO OPTIONAL LAMP OR SONALERT
4
Bendix/King
KTA 870/KMH 880 P10 KTA 970/KMH 980
54
CDU 429 A TX 10
55
CDU 429 B TX
2
TAS TEST IN
23
TAS STBY
L3 Communications SKY 497
P1
SOFTWARE V1.6 OR HIGHER
34
429 TX 1A
33
429 TX 1B 11
85
SOFT KEY 1 (TEST/ALT)
82
SOFT KET 4 (OPR/STB)
11
POWER SWITCH HI
3
POWER SWITCH LO
L3 Communications
P1
SKY 899
42
429 TX 1A
43
429 TX 1B 11
10
DISPLAY GROUND
19
SOFT KEY 1 (TEST/ALT)
21
SOFT KET 4 (OPR/STB)
4
POWER SWITCH HI
5
POWER SWITCH LO
Ryan 9900B/BX
TAS6XX
P1
TCAD Processor
19
RS-232 RX 2
17
RS-232 TX 2
18
RS-232 GROUND 2
5
REMOTE MUTE
6
TRAFFIC ANNUNCIATE OUT
16
SWITCH
P8001
14 15
GTS 8XX
ARINC 429 OUT 1A
12
ARINC 429 OUT 1B
16
ARINC 429 IN 1A
17
ARINC 429 IN 1B
ANNUNCIATE E
11
ANNUNCIATE D
10
P1050 13
TAWS AUDIO ACTIVE OUT
15
P8002
75
TRAFFIC OPERATE/STANDBY
74
SELF TEST SELECT
11
TAWS AUDIO ACTIVE OUT
Figure D - 14: Traffic Advisory Interconnect Page 1 of 2
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IFD5XX/4XX Installation Manual
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. IF THE GPS ARINC 429 IN 1 PORT (P1001-48 AND -49) IS ALREADY USED FOR ANOTHER PURPOSE. THE GPS ARINC 429 IN 2 PORT (P1001-50 AND -51) MAY BE CONNECTED INSTEAD. 3. THE SKYWATCH POWER SWITCH PINS, SHOWN ON P1, SHOULD BE CONNECTED TOGETHER TO TURN THE PROCESSOR UNIT ON AND DISCONNECTED TO TURN IT OFF. IF A SKYWATCH CONTROL/DISPLAY UNIT IS NOT IN THE INSTALLATION, A DEDICATED SWITCH MAY BE REQUIRED TO TURN THE SKYWATCH PROCESSOR UNIT ON OR OFF. 4. THE AVIDYNE/RYAN TAS PROCESSOR SWITCH PIN (P1-16) SHOULD BE GROUNDED TO TURN THE PROCESSOR UNIT ON, AND OPEN TO TURN THIS UNIT OFF. IF A RYAN TCAD DISPLAY UNIT IS NOT IN THE INSTALLATION, A DEDICATED SWITCH MAY BE REQUIRED TO TURN THE TAS PROCESSOR UNIT ON AND OFF. 5. IF ANY OF THESE TRAFFIC SYSTEMS ARE INSTALLED WITHOUT A CONTROL/DISPLAY UNIT, A PLACARD IS REQUIRED NEAR THE IFD 5XX/4XX UNIT, INDICATING THAT A TRAFFIC ADVISORY SYSTEM IS INSTALLED, AND ITS DATA MAY BE DISPLAYED ON THE IFD5XX/4XX UNIT. 6. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER INPUTS SHOWN FOR REFERENCE ONLY. 7. IN ORDER FOR SKYWATCH DATA TO BE DISPLAYED ON THE IFD5XX/4XX UNIT'S MAP PAGE, THE IFD5XX/4XX UNIT MUST HAVE A DIGITAL HEADING SOURCE, OR THE SKYWATCH MUST HAVE A SYNCHRO OR SERIAL HEADING SOURCE. A STEPPER HEADING SOURCE WILL NOT ALLOW SKYWATCH DATA TO BE DISPLAYED ON THE MAP PAGE. 8. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL. 9. REFER TO SECTION 7.0 FOR ARINC 429 AND FOR RS-232 SETTINGS. IF AN ARINC 429 TRAFFIC SOURCE IS USED, THE CORRESPONDING ARINC 429 INPUT MUST BE SET TO HIGH SPEED. 100. KTA 870/KMH 880/KTA 970/KMH 980 SYSTEMS MUST HAVE TRAFFIC CONFIGURED FOR "CONTROLLER TYPE: DISCRETE" AND "DISPLAY VALID: IGNORE". 111. SKYWATCH MUST BE CONFIGURED FOR AN ARINC 735 TYPE 1 DISPLAY. 122. FOR GTX 8XX CONFIGURATION SETTINGS, SEE THE GTX 8XX INSTALLATION MANUAL. 13 THE P1050 CONNECTOR IS NOT AVALIABLE ON IFD4XX UNITS.
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IFD5XX/4XX Installation Manual
IFD5XX/4XX #1
6
P1001
GPS ARINC 429 OUT 1 A
46
GPS ARINC 429 OUT 1 B
47
GPS ARINC 429 IN 1 A
48
GPS ARINC 429 IN 1 B
49
ANNUNCIATE E
11
IFD5XX/4XX #2
6
GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B
P1001
48 49
ANNUNCIATE E
11
GARMIN 7 P3301 GTX 330(ES)/330D(ES)
32 35
GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B
3
30 28
GPS ARINC 429 OUT 2 A GPS ARINC 429 OUT 2 B
4
46
TIS CONNECT SELECT
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARDEDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE. THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. ARINC 429 IN 1 (P3301-32 AND -35) INPUT ALLOWS AUTOMATED START AND STOP OF FLIGHT TIMER AND PLACES THE TRANSPONDER IN GROUND (GND) MODE UPON LANDING.
4. IF EXTERNAL STBY SELECT IS CONNECTED IN THIS INSTALLATION USE GTX 330 ARINC 429 OUT 1 A AND 1 B, (PINS 37 AND 34) RATHER THAN ARINC 429 OUT 2 A AND 2 B (PINS 30 AND 28) SHOWN. ALTITUDE DATA WILL NOT BE TRANSMITTED OVER ARINC 429 PORT 2 TO THE IFD540/440 UNIT WHEN EXTERNAL STBY SELECT IS GROUNDED.
5. WHEN TIS IS USED IN THE AIRCRAFT DO NOT CONNECT ANOTHER TRAFFIC SYSTEM TO THE SAME IFD540/440 UNIT.
6. IFD540/440 SETUP:
MAIN ARINC 429 CONFIG: IN 1: HIGH, GARMIN GTX 330 OUT: SET TO MATCH INSTALLATION
7. GTX 330 SETUP:
429 INPUT CHANNEL 1: GPS (SPEED SET TO MATCH IFD540/440 #1 OUTPUT) 429 OUTPUT CHANNEL 2: GARMIN W/TIS
Figure D - 15: GTX 330 Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX 5
P1001
GPS RS-232 OUT 4
54
GPS RS-232 IN 4
55
3
OPTIONAL EXTERNAL CLEAR SWITCH
L3 Communications
P3
WX-500 5
8
RS-232 RX
20
RS-232 TX
6
EXTERNAL CLEAR
P2
5
RS-232 GROUND
IFD5XX/4XX 5
P1001
4 GPS RS-232 OUT 1
56
Bendix/King KGP 560 GA Enhanced GPWS
P1
6
GPS_RXA
IFD5XX/4XX
5
P1001
6
GPS RS-232 IN 2
59
GPS RS-232 OUT 2
58
GARMIN GDL 69/69A Satellite Data Link
P691
7
3
RS-232 OUT 3
6
RS-232 IN 3
11
SIGNAL GROUND
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARDEDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE. THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. IN ORDER FOR WX-500 DATA TO BE DISPLAYED ON THE IFD540 UNIT'S MAP PAGE, THE IFD540/440 MUST HAVE A DIGITAL HEADING SOURCE, OR THE WX-500 MUST HAVE A SYNCHRO OR SERIAL HEADING SOURCE. A STEPPER HEADING SOURCE WILL NOT ALLOW WX-500 DATA TO BE DISPLAYED ON THE MAP PAGE.
4. IF AN RS-232 OUTPUT PORT IS CONFIGURED FOR THE HONEYWELL EGPWS, THE CORRESPONDING RS-232 INPUT OF THE SAME PORT MAY NOT BE USED.
5. REFER TO SECTION 7.0 FOR RS-232 CHANNEL SETTINGS.
6. CONNECTION TO RS-232 PORT #2 OF THE IFD540/440 UNIT IS SHOWN. IF PORT #2 IS ALREADY IN USE, ANY OTHER AVAILABLE RS-232 PORT MAY BE USED AS WELL.
7. CONNECTION TO RS-232 PORT #2 OF THE GDL 69/69A MAY BE USED AS WELL.
8. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUT OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
Figure D - 16: Terrain and Weather Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX 4
P1001
3
GPS RS-232 IN 2
59
GPS RS-232 OUT 2
58
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
Avidyne TWX670
J1
20
RS232 TX1 - DISPLAY
18
RS232 RX1 - DISPLAY
19
GROUND
32
ARINC RX1+ A
31
ARINC RX1- B
IFD5XX/4XX
4
P1001
3
GPS RS-232 IN 2
59
GPS RS-232 OUT 2
58
AVIDYNE MLB700
P1
2 3
24
WSI AV300/
350
P1
2 3
24
DATALINK
RS-232 OUT 1 RS-232 IN 1 SIGNAL GROUND
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD540/440 UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARDEDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE. THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
33.
CONNECTION TO RS-232 PORT #2 OF THE IFD540/440 UNIT IS SHOWN. IF PORT #2 IS ALREADY IN USE,
ANY OTHER AVAILABLE RS-232 PORT MAY BE USED AS WELL.
4. REFER TO SECTION 7.0 FOR RS-232 CHANNEL SETTINGS.
600-00299-000
Figure D - 17: Weather Interconnect
Page 186 of 259
Revision: 17
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1002
4
COM AUDIO HI
7
COM AUDIO LO
19
COM MIC AUDIO HI
6
2
COM MIC KEY
4
COM MIC AUDIO LO
18
INTERCOM MIC HI
5
2
INTERCOM MIC LO
17
GARMIN
SL 10 SERIES GMA 340 SL 15 SERIES
BOTTOM
P1
GMA 347 J3471
9/(10) GND LUG
P(H) R(V) GND LUG
9/(13) 10/(14)
11/(15) 12/(30) 10/(14)
7/(12) 8/(13)
26/(32) 27/(33) 8/(13)
INTERCOM MIC 5 6
INTERCOM MIC LO
AVIDYNE
AMX240
J1
9/(13) 10/(14) 11/(15) 12/(30) 10/(14)
PS ENGINEERING
PMA 8000(B/BT)
PMA 6000 PMA 7000
J1 (BOTTOM)
BOTTOM
KMA 24 P241
Bendix/King
KMA 26
KMA 28
KMA 24H -70/-71
P261 J1 (BOTTOM) P241
AUDIO PANEL
9/(13) 10/(14)
11/(15) 12/(30) GND LUG
9/(10) GND LUG
P/(H) R/(V) GND LUG
9/(10) GND LUG
4/(5) 21/(22)
9/(10) GND LUG
P/(H)
37/(39)
R/(V)
38/(40)
GND LUG GND LUG
P/(H) R/(V) GND LUG
T/(16) GND LUG
3/(E) C/(H) GND LUG
COM 1/(COM 2) AUDIO HI COM 1/(COM 2) AUDIO LO
COM 1/(COM 2) MIC AUDIO COM 1/(COM 2) MIC KEY COM 1/(COM 2) MIC AUDIO LO
COM REMOTE TRANSFER
15
COM TRANSFER SWITCH
7
P1006
10
4
VOR/ILS AUDIO HI VOR/ILS AUDIO LO
16 17
10
4
STBY COM AUDIO HI STBY COM AUDIO LO
7 34
VLOC REMOTE TRANSFER
28
VLOC TRANSFER SWITCH
12/(13) GND LUG
NA NA
17/(19) 18/(20)
NA NA
6/(14) 25/(34)
NA NA
17/(19) 18/(20)
7(21) 8(22)
17/(19) 18/(20)
NA NA .
12/(13) GND LUG
NA NA
12/(13) GND LUG
NA NA
7/(8) 24/(25)
NA NA
12/(13) GND LUG
NA NA
P/(13) GND LUG
NA NA
NAV 1/(NAV 2) AUDIO HI NAV 1/(NAV 2) AUDIO LO
MON1(MON 2) AUDIO IN MON 1(MON 2) AUDIO LO
Figure D - 18: Audio Panel Interconnect Page 1 of 2
UP793797
600-00299-000
Page 187 of 259
Revision: 17
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
NOTES:
1.
ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2.
CONNECTING TWO MICROPHONES TO MIC AUDIO HI/LO OR INTERCOM MIC HI/LO AT THE SAME TIME
MAY RESULT IN WEAK OR DISTORTED AUDIO. MIC ISOLATION RELAYS ARE RECOMMENDED SO THAT
ONLY ONE MIC IS ACTIVE AT A TIME.
3.
RESERVED
44.
IF THE AUDIO PANEL DOES NOT HAVE A LO INPUT. IT SHOULD BE CONNECTED TO A GROUND LUG AT
THE AUDIO PANEL.
5.
THE IFD540/440 INTERCOM FUNCTION SHOULD ONLY BE USED IF THERE IS NO OTHER INTERCOM
SYSTEM IN THE AIRCRAFT.
6.
INTERCOM WIRING OPTION:
IFD540/440 P1002
COM MIC KEY
4
COM MIC AUDIO HI
6
INTERCOM MIC HI
5
COM MIC AUDIO
18
MICROPHONE SWITCH (DPDT)
COM
MIC JACK
NC
INTERCOM
77.
THE COM REMOTE TRANSFER INPUT (P1002-15) MAY BE USED FOR EMERGENCY OPERATION OF THE
COM TRANSMITTER. IF THE REMOTE TRANSFER SWITCH IS ACTIVE FOR THREE SECONDS, THE ACTIVE
COM FREQUENCY WILL CHANGE TO 121.50 MHZ.
8.
REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT
INFORMATION. PINOUT OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
9.
SHIELDS FOR AUDIO CABLES SHOULD BE GROUNDED AT ONE END (WITH LEADS LESS THAN 3.0
INCHES) AND LEFT FLOATING AT THE OTHER END. IF SHIELDED AUDIO CABLE IS CARRIED THROUGH
DISCONNECT, CARRY SHIELD GROUND THROUGH DISCONNECT ON SEPARATE PIN.
10
NOT APPLICABLE FOR IFD510/545/410
Page 2 of 2
UP793797
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Page 188 of 259
Revision: 17
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1006
VOR/LOC +LEFT
5
VOR/LOC +RIGHT
6
VOR/LOC +TO
1
VOR/LOC +FROM
2
VOR/LOC +FLAG
3
VOR/LOC -FLAG
4
VOR/LOC SUPERFLAG
15
VOR/LOC COMPOSITE OUT
8
ILS ENERGIZE
29
GLIDESLOPE +UP
32
GLIDESLOPE +DOWN/-FLAG
31
GLIDESLOPE +FLAG
30
GLIDESLOPE SUPERFLAG
38
VOR OBS ROTOR H
10
VOR OBS ROTOR C
9
COR OBS STATOR D
13
VOR OBS STATOR E/G
11
VOR OBS STATOR F
12
GARMIN
GI 102/A GI 106/A
P1
P1
KI 202 P2021
11
11
n
12
12
j
9
9
e
10
10
S
7
7
N
8
8
F
-
-
-
-
-
-
-
-
-
-
-
-
-
13
-
-
14
-
-
15
-
-
16
-
-
-
-
-
-
-
1
1
c
2
2
Z
3
3
L
5
5
P
4
4
T
6
6
W
KI 206
P2061
n j
e S
N F
-
-
k m
H J
-
c Z
L P
T W
KI203
P2031
-
-
-
Y
K
-
-
-
-
-
-
Bendix/King
KI204
KI 208
P2041
P2081
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
Y
2
K
4
k
-
m
-
H
-
J
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
KI 209 P2091
KI 208A P208A1
KI 209A P209A1
Navigation Indicator
-
-
-
+LEFT
-
-
-
+RIGHT
-
-
-
+TO
-
-
-
+FROM
-
-
-
NAV +FLAG
-
-
-
NAV -FLAG
-
-
-
NAV SUPERFLAG
-
-
-
NAV SUPERFLAG LO
2
6
6
VOR/LOC COMPOSITE
4
10
10
ILS ENERGIZE
3
-
29
+UP
6
-
28
+DOWN
9
-
25
GLIDESLOPE +FLAG
12
-
24
GLIDESLOPE -FLAG
-
-
-
GLIDESLOPE SUPERFLAG
-
-
-
GLIDESLOPE SUPERFLAG LO
-
-
-
OBS A/H
-
-
-
OBS C
-
-
-
OBS D (COS HI)
-
-
-
OBS E (COS LO)
-
-
-
OBS F (SIN HI)
-
-
-
OBS G (SIN LO)
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. THIS INTERCONNECT APPLIES ONLY WHEN IT IS DESIRED FOR A SEPARATE INDICATOR TO DISPLAY IFD540/440 VOR/ILS INFORMATION (REGARDLESS OF THE SELECTED NAVIGATION SOURCE).
3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
4. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
5.
NOT APPLICABLE FOR IFD510/545/410
Figure D - 19: VOR/ILS Indicator Interconnect
UP793797
600-00299-000
Page 189 of 259
Revision: 17
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN +LEFT 21 MAIN +RIGHT 22
MAIN +TO 25 MAIN +FROM 26
MAIN LATERAL +FLAG 23 MAIN LATERAL -FLAG 24
MAIN LATERAL SUPERFLAG 17
MAIN +UP 27 MAIN +DOWN 28
MAIN VERTICAL +FLAG 29 MAIN VERTICAL -FLAG 30
MAIN VERTICAL SUPERFLAG 18
MAIN OBS ROTOR H 32 MAIN OBS ROTOR C 31
MAIN OBS STATOR D 33 MAIN OBS STATOR E 34
MAIN OBS STATOR F 35 MAIN OBS STATOR G 36
GPS ANNUNCIATE 2 VLOC ANNUNCIATE 1 ILS/GPS APPROACH 14
GARMIN
S-TEC
BENDIX KING
CENTURY
COLLINS
GI 102 (X) GI106 GI106A ST 180 KI 206
KI 525A
KPI 552/B NSD360A KPI 553/A/B NSD1000 331A-6P
331A-9G
P1
P1 P1
P2 P2061 P1 P2
P101
CD132
P1
P1 P2
11
11 11
27
n
V-
i
17
12
12 12
43
j
b
-
h
18
9
9
9
26
e
Z
-
j
33
10
10 10
42
S
T
-
k
34
7
7
7
37
N
K
-
f
31
8
8
8
38
F
F
-
g
32
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
13 13
44
k
-E
JJ
27
-
14 14
28
m
-B
HH
28
-
15 15
36
H
-
J
FF
30
-
16 16
35
J
W-
GG
29
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
1
1
1
22
c
-X
W
15
2
2
2
24
Z
-
a
N,V
16
3
3
3
25
L
-V
Z
24
5
5
5
39
P
-Y
A
23
4
4
4
40
T
-
b
Y
26
6
6
6
41
W
-
e
X
25
29
-
4
28
-
3
26
-
1
27
-
2
31
-
-
32
-
-
-
- 37
-
- 38
33
-
5
34
-
6
35
-
-
36
-
-
-
-
7
-
-
-
1
1
-
3
3
-
4
4
-
5
5
-
6
6
-
7
7
-
PN-101
P1
j i
n p
k m
r q
s t
-
a c
d e
f g
RD 444
SPERRY RD550A
P1 P2 P1 P2
-
F
-
F
-
E
-
E
-
A
-
A
-
B
-
B
-
-
-
-
-
-
-
-
-
P
-
P
-
S
-
S
-
C
-
C
-
D
-
D
-
-
-
-
-
-
-
-
-
U
-
U
-
W
-
W
DD - DD FF - FF -
Z
-
Z
-
AA - AA -
BB - BB CC - CC -
MID CONTINENT
RD650
MD2 MD2 22- 22402 406
P1 P2 P1 P1
Navigation Indicator
-
4
22 22 +LEFT
-
3
23 23 +RIGHT
-
1
16 16 +TO
-
2
17 17 +FROM
-
-
20 20 NAV +FLAG
-
-
21 21 NAV -FLAG
39 -
- 36
-
5
-
6
-
- NAV SUPERFLAG
-
- NAV SUPERFLAG LO
- 25 +UP
- 24 +DOWN
-
-
-
-
- 18 G/S +FLAG - 19 G/S -FLAG
38 -
-
- G/S SUPERFLAG
-
8
-
- G/S SUPERFLAG LO
6
-
8
-
1
1 OBS A/H
2
2 OBS C
9
-
10 -
3
3 OBS D (COS HI)
5
5 OBS E (COS LO)
11 12 -
6
6 OBS F (SIN HI)
4
4 OBS G (SIN LO)
-
-
17
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
15 15 GPS ANNUNCIATOR
-
-
18
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
8
8 VLOC ANNUNCIATOR
-
-
-
-
-
-
-
-
-
-
-
-
-
a
-
-
-
- 47
-
- ILS ENERGIZE
NOTES:
1.
ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2.
REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS
SHOWN FOR REFERENCE ONLY.
3.
AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE
SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO
AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
4.
LOWER CASE PIN DESIGNATORS ARE SHOWN AS UNDERLINED LETTERS.
Figure D - 20: Main Indicator Interconnect
600-00299-000
Page 190 of 259
Revision: 17
UP793797
RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN +TO
25
MAIN +FROM
26
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
MAIN +UP
27
MAIN +DOWN
28
MAIN VERTICAL +FLAG
29
MAIN VERTICAL -FLAG
30
PRECISION APPROACH
14
MAIN OBS ROTOR H
32
MAIN OBS ROTOR C
31
MAIN OBS ROTOR D
33
MAIN OBS ROTOR E
34
MAIN OBS ROTOR F
35
MAIN OBS ROTOR G
36
10k OHM 10k OHM
2
GPS ANNUNCIATE
2
VOR/LOC COMPOSITE OUT
P1006
8
ILS ENERGIZE
29
7
GLIDESLOPE +UP
32
GLIDESLOPE +DOWN / -FLAG
31
GLIDESLOPE +FLAG
30
VOR/ILS
6
GPS
Bendix/King KI 209A
Navigation Indicator
P209A1
20
LNAV LATERAL DEV +LT IN
21
LNAV LATERAL DEV +RT IN
43
LNAV +TO IN
42
LNAV +FROM IN
48
LNAV LATERAL +FLAG IN
3
LNAV LATERAL -FLAG IN
27
LNAV VERTICAL +UP IN
26
LNAV VERTICAL +DOWN IN
23
LNAV VERTICAL +FLAG IN
22
LNAV VERTICAL -FLAG IN
9
LNAV FCS LOC ENGAGE IN
50
OBS RETURN
2
LNAV OBS EXCITATION IN
15
LNAV OBS SIN OUT
14
LNAV OBS COS OUT
5
RELAY ENGAGE
6
VOR/LOC COMPOSITE
10
NAV LOC ENGAGE IN
29
NAV VERTICAL +UP IN
28
NAV VERTICAL +DOWN IN
25
NAV VERTICAL +FLAG IN
24
NAV VERTICAL -FLAG IN
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2
TO CONNECT THE IFD5XX/4XX TO A KI209A INDICATOR, ADD TWO 10K OHM, ¼ WATT RESISTORS AS SHOWN.
3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
4. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
PROPER CONNECTION OF THE RELAY ENGAGE INPUT OF THE KI 209A IS DEPENDENT ON ITS POWER SUPPLY VOLTAGE. REFER TO KI 209A 5 DOCUMENTATION FOR PROPER CONNECTION.
IF THE IFD5XX/4XX IS INSTALLED, AND ANOTHER VOR/ILS RECEIVER IS AVAILABLE TO DRIVE THE NAVIGATION INDICATOR, AN EXTERNAL
6
SOURCE SELECTION SWITCH MUST BE USED IN LIEU OF THE GPS ANNUNICATE OUTPUT.
7
NOT APPLICABLE FOR IFD 510/545/410
Figure D - 21: Main Indicator KI209 Interconnect
UP793797
600-00299-000
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN +TO
25
MAIN +FROM
26
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
APPROACH ANNUNCIATE
5
MAIN OBS ROTOR H
32
MAIN OBS ROTOR C
31
MAIN OBS ROTOR D
33
MAIN OBS ROTOR E
34
MAIN OBS ROTOR F
35
MAIN OBS ROTOR G
36
10k OHM 10k OHM
2
GPS ANNUNCIATE
2
P1006
7
VOR/LOC COMPOSITE OUT
8
ILS ENERGIZE
29
VOR/ILS
6
GPS
Bendix/King KI 208A P208A1
Navigation Indicator
20
LNAV LATERAL DEV +LT IN
21
LNAV LATERAL DEV +RT IN
43
LNAV +TO IN
42
LNAV +FROM IN
48
LNAV LATERAL +FLAG IN
3
LNAV LATERAL -FLAG IN
9
LNAV FCS LOC ENGAGE IN
50
OBS RETURN
2
LNAV OBS EXCITATION IN
15
LNAV OBS SIN OUT
14
LNAV OBS COS OUT
5
RELAY ENGAGE
6
VOR/LOC COMPOSITE
10
NAV LOC ENGAGE IN
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2
TO CONNECT THE IFD5XX/4XX TO A KI209A INDICATOR, ADD TWO 10K OHM, ¼ WATT RESISTORS AS SHOWN.
3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
4. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
5
PROPER CONNECTION OF THE RELAY ENGAGE INPUT OF THE KI 208A IS DEPENDENT ON ITS POWER SUPPLY VOLTAGE. REFER TO KI 208A
DOCUMENTATION FOR PROPER CONNECTION.
6
IF THE IFD540/440 IS INSTALLED, AND ANOTHER VOR/ILS RECEIVER IS AVAILABLE TO DRIVE THE NAVIGATION INDICATOR, AN EXTERNAL
SOURCE SELECTION SWITCH MUST BE USED IN LIEU OF THE GPS ANNUNICATE OUTPUT.
7 NOT APPLICABLE TO IFD 510/545/410
Figure D - 22: Main Indicator KI208 Interconnect
UP793797
600-00299-000
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN +TO
25
MAIN +FROM
26
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
GPS ANNUNCIATE
2
VLOC ANNUNICATE
1
MAIN +UP
27
MAIN +DOWN
28
MAIN VERTICAL +FLAG
29
MAIN VERTICAL -FLAG
30
OBS ROTOR H
32
OBS ROTOR C
31
OBS STATOR D
33
OBS STATOR E
34
OBS STATOR F
35
OBS STATOR G
36
200-202/ -302
J1
Mid-Contient
200-203/ 200-206/
-303
-306
J1
J1
200-207/ -307
J1
Navigation Indicator
11
11
11
11
+LEFT
12
12
12
12
+RIGHT
9
9
9
9
+TO
10
10
10
10
+FROM
7
7
7
7
NAV +FLAG
8
8
8
8
NAV -FLAG
17
17
17
17
GPS ANNUNCIATOR
5
18
18
18
18
VLOC ANNUNCIATOR
-
-
13
13
+UP
-
-
14
14
+DOWN
-
-
15
15
GLIDESLOPE +FLAG
-
-
16
16
GLIDESLOPE -FLAG
1
1
1
1
RESOLVER H
2
2
2
2
RESOLVER C
3
3
3
3
RESOLVER D
5
5
5
5
RESOLVER E
4
4
4
4
RESOLVER F
6
6
6
6
RESOLVER G
NOTES:
1.
ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2.
THE 200-202/-203/-302/-303 DOES NOT HAVE VERTICAL DEVIATION INDICATOR. DO NOT USE FOR IFR
NAVIGATION.
3.
REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION.
PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
4.
AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE
CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS
THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A
CONDUCTOR AS PRACTICAL.
5
NAVIGATION ANNUNCIATION
Figure D - 23: Main Indicator MD200-20X/-30X Interconnect
UP793797
600-00299-000
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RELEASED FOR THE EXCLUSIVE USE BY: HONEYWELL EMPLOYEE AMERICAS
IFD5XX/4XX Installation Manual
IFD5XX/4XX P1001
2
MAIN OBI CLOCK
43
MAIN OBI DATA
44
MAIN OBI SYNC
45
KI 229 P2291
12 19 11
Bendix/King
KNI 582 Pointer #1
P5821
KNI 582 Pointer #2
P5821
8
7
17
16
33
24
KDA 692 P6921
Radio Magnetic Indicator
11
OBI CLOCK
L
OBI DATA
M
OBI SYNC
IFD5XX/4XX P1006
VOR OBI CLOCK
25
6
VOR OBI DATA
27
VOR OBI SYNC
26
P1001
MAIN OBI CLOCK
43
MAIN OBI DATA
44
MAIN OBI SYNC
45
3
VLOC
GPS
KI 229 P2291
12 19 11
Bendix/King
KNI 582 Pointer #1
P5821
KNI 582 Pointer #2
P5821
8
7
17
16
33
24
KDA 692 P6921
Radio Magnetic Indicator
11
OBI CLOCK
L
OBI DATA
M
OBI SYNC
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. IF IT IS DESIRED FOR THE RMI POINTER TO SWITCH WITH THE CDI BUTTON ON THE FRONT PANEL OF THE IFD540/440. INSTALL AS PER THE TOP DIAGRAM. AND SELECT TRACK CDI FOR THE OBI SOURCE FIELD OF THE MAIN CDI/OBS CONFIG PAGE.
33.
IF IT IS DESIRED TO USE A SEPARATE SWITCH FOR THE RMI POINTER, INSTALL AS PER BOTTOM DIAGRAM AND SELECT ALWAYS GPS FOR THE OBI SOURCE FIELD OF THE MAIN CDI/OBS CONFIG PAGE.
4. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
5. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
6
NOT APPLICABLE FOR IFD510/545/410
Figure D - 24: RMI/OBI Interconnect
600-00299-000
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IFD5XX/4XX Installation Manual
IFD5XX/4XX #1
P1006
3
SERIAL DME DATA
19
SERIAL DME CLOCK
18
SER DME-CHAN REQ/PAR DME-4MHZ
20
DME COMMON
22
SER DME-RNAV MODE/PAR DME-2MHZ
21
N/C
NAV 1 NAV 2
Bendix/King
KN 62/62A
KN 64
P621/P62A1
P641
13
13
14
14
L
L
C
C
DME
DATA BUS CLOCK BUS RNAV/CHANNEL REQUEST DME COMMON
IFD5XX/4XX #2
P1006
3
SERIAL DME DATA
19
SERIAL DME CLOCK
18
SER DME-CHAN REQ/PAR DME-4MHZ
20
DME COMMON
22
SER DME-RNAV MODE/PAR DME-2MHZ
21
N/C
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. THE IFD5XX/4XX MUST BE CONFIGURED AT INSTALLATION TO OUTPUT KING SERIAL DME TUNING DATA UNDER THE DME CHANNEL MODE.
3 4. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF
OTHER UNITS SHOWN FOR REFERENCE ONLY.
5. NOT APPLICABLE FOR IFD510/545/410
Figure D - 25: King Serial DME Tuning Interconnect, Panel Mount
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IFD5XX/4XX Installation Manual
IFD5XX/4XX #1
P1006
3
SERIAL DME DATA
19
SERIAL DME CLOCK
18
SER DME-CHAN REQ/PAR DME-4MHZ
20
DME COMMON
22
SER DME-RNAV MODE/PAR DME-2MHZ
21
N/C
IFD5XX/4XX #2
P1006
3
SERIAL DME DATA
19
SERIAL DME CLOCK
18
SER DME-CHAN REQ/PAR DME-4MHZ
20
DME COMMON
22
SER DME-RNAV MODE/PAR DME-2MHZ
21
N/C
Bendix/King
KDI 572
KDI 574
P5721
P5741
11
11
DME
DATA BUS
12
12
CLOCK BUS
17
17
RNAV REQUEST
N/C
33
33
10 BIT/50 BIT SELECT
48
48
NAV 1 COMMON
49
49
NAV 2 COMMON
15
15
DME REQUEST
Bendix/King
KN 63
KDM 706
P631
P7061
6
9
F
8
D
24
DME
DATA BUS CLOCK BUS DME REQUEST
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. THE IFD540/440 MUST BE CONFIGURED AT INSTALLATION TO OUTPUT KING SERIAL DME TUNING DATA UNDER THE DME CHANNEL MODE.
3 4. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER
UNITS SHOWN FOR REFERENCE ONLY.
5. NOT APPLICABLE FOR IFD 510/545/410
Figure D - 26: King Serial DME Tuning Interconnect, Remote Mount
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
PARALLEL DME-8MHZ SER DME-CHAN REQ/PAR DME-4MHZ SER DME-RNAV MODE/PAR DME-3MHZ
PARALLEL DME-1MHZ
PARALLEL DME-800KHZ PARALLEL DME-400KHZ PARALLEL DME-200KHZ PARALLEL DME-100KHZ
PARALLEL DME-50KHZ
DME COMMON
P1006
14 20 21 33
37 39 40 42
43
22
N/C N/C
Bendix/King
KN 62A
P621
12 9 8 11 7 4 6 H 5
C
-
J D M
Collins
DME 40
DME 42
P1
P1
28
28
-
-
32
32
43
43
35
35
11
11
-
-
19
19
27
27
12
12
44
44
6
6
52
52
51
51
-
48/50
-
-
-
-
S-Tec
TCR-451
P1
28 29 30 31 32 33 34 35 36
16
-
-
Narco
DME 890
IDME 891
P301
P301
2
31
3
12
4
30
5
11
-
-
B
28
C
9
D
27
E
8
-
-
H
32
1
35
-
-
-
-
-
-
-
-
-
-
ARC
RTA-476A
P2
11 10 9 8 24 23 22 21 7
25
-
-
DME
1 MHZ-A 1 MHZ-B 1 MHZ-C 1 MHZ-D 1 MHZ-E 100 KHZ-A 100 KHZ-B 100 KHZ-C 100 KHZ-D 100 KHZ-E 50 KHZ
DME COMMON
10 MHZ-A 10 MHZ-E
2 X 5 CODE SELECT SLIP CODE SELECT BCD CODE SELECT
NOTES:
2
2
25
2
3
3
3
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
22.
THE IFD5XX/4XX MUST BE CONFIGURED FOR PARALLEL 2X5 DME CHANNELING MODE FOR PROPER OPERATION WITH THIS MODEL
OF
DME TRANSCEIVER.
33.
THE IFD540/440 MUST BE CONFIGURED FOR NARCO 890/891 DME CHANNELING MODE FOR PROPER OPERATION WITH THIS MODEL
OF DME TRANSCEIVER.
4. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
5. DME 42 MUST BE STRAPPED FOR 2X5 TUNING. REFER TO DME 42 INSTALLATION MANUAL FOR STRAPPING INFORMATION.
6. NOT APPLICABLE FOR IFD 510/545/410
Figure D - 27: Parallel DME Tuning Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
2 P1006
PARALLEL DME-8MHZ
14
SER DME-CHAN REQ/PAR DME-4MHZ
20
SER DME-RNAV MODE/PAR DME-2MHZ
21
PARALLEL DME-1MHZ
33
PARALLEL DME-800KHZ
37
PARALLEL DME-400KHZ
39
PARALLEL DME-200KHZ
40
PARALLEL DME-100KHZ
42
PARALLEL DME-50KHZ
43
DME COMMON
22
Bendix/King
KN 61
KN 65
P611
P651
4
14
3
15
2
16
1
17
9
32
8
33
7
34
6
35
10
36
12
22
Parallel Slip Code Tuned DME
M0 M1 M2 M3
K0 K1 K2 K3
K50
DME COMMON
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. THE IFD540 MUST BE CONFIGURED TO OUTPUT SLIP CODE DME TUNING DATA FOR PROPER OPERATION IN THIS CONFIGURATION.
3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
4. NOT APPLICABLE FOR IFD510/545/410
600-00299-000
Figure D - 28: Parallel DME Tuning Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX /4XX
P1050
TERRAIN NOT AVAIL ANNUNCIATE
9
TERRAIN WARNING ANNUNCIATE
10
TERRAIN CAUTION ANNUNCIATE
11
TAWS INHIBIT ANNUNCIATE
12
TAWS INHIBIT INPUT
1
GROUND
17
GROUND
18
GROUND
19
GROUND
20
GROUND
21
TAWS AUDIO ACTIVE OUT
15
4
GARMIN 013-0079-XX
J1
MID-CONTINENT MD41-10XX J1
TAWS ANNUNCIATOR PANEL 2
10
10
TERR N/A ANNC IN
11
11
TERR PULL UP ANNC IN
5
5
TERR CAUTION ANNC IN
19
19
TAWS INHIBIT ANNC IN
20
20
TAWS INHIBIT OUT
21
21
AIRCRAFT GROUND
22
22
AIRCRAFT GROUND
23
23
AIRCRAFT GROUND
24
24
AIRCRAFT GROUND
25
25
AIRCRAFT GROUND
P1001 3
TAWS AUDIO OUT HI
52
TAWS AUDIO OUT LO
53
GARMIN
PS Engineering
Avidyne
Bendix/King
AUDIO PANEL
SL15
GMA 340 GMA 347 PMA 6000 PMA 8000 AMX240 KMA 24 KMA 26
6
SL15M
PMA 7000
(B/BT)
KMA 28
5
Bottom
J1
J3471
Bottom
J1
J1
Bottom
P261
T
31
GND Lug
32
54
T
31
55
GND Lug
32
31
T
14
UNSWITCHED IN HI
32
GND Lug
31
UNSWITCHED IN LO
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. THE TERRAIN ALERTING ON THE IFD5XX/4XX DOES NOT SATISFY ANY PART 91/135 REQUIRMENT FOR A TAWS SYSTEM. INSTALLING AN EXTERNAL ANNUNCIATOR IS NOT REQUIRED.
3. WHEN TWO TAWS-EQUIPPED UNITS ARE INSTALLED IN AN AIRCRAFT, ONLY ONE SHOULD UTILIZE P1001-52/53 TO AVOID COMPETING AUDIO MESSAGES.
4. CONNECT TO THE AUDIO INHIBIT INPUTS OF OTHER SYSTEMS WITH LOWER PRIORITY AURALS THAN TAWS. THIS CONNECTOR IS NOT AVAILABLE ON THE IFD4XX.
55.
SHIELDS FOR AUDIO CABLES SHOULD BE GROUNDED AT ONE END (WITH LEADS LESS THAN 3.0 INCHES) AND LEFT
FLOATING AT THE OTHER END. IF SHIELDED AUDIO CABLE IS CARRIED THROUGH A DISCONNECT, CARRY SHIELD GROUND
THROUGHOUT DISCONNECT ON A SEPARATE PIN.
66.
OTHER UNSWITCHED INPUTS ON THE AUDIO PANEL MAY BE USED IN LIEU OF THOSE SHOWN.
7. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
Figure D - 29: TAWS Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX 5
MAIN LATERAL +FLAG MAIN LATERAL -FLAG
MAIN +LEFT MAIN +RIGHT
MAIN VERTICAL +FLAG MAIN VERTICAL -FLAG
MAIN +UP
MAIN +DOWN
4
{ GPS ARINC 429 OUT
A B
P1001
23 24
21 22
29 30
27 28
46 47
ILS/GPS APPROACH
14
LAT +FLAG LAT -FLAG LAT +LEFT LAT +RIGHT VERT +FLAG VERT -FLAG VERT +UP VERT +DOWN
TO MAIN CDI
AUTOPILOT COMPUTER
LAT DEV +FLAG LAT DEV -FLAG
LAT DEV +LT LAT DEV +RT
GS DEV +FLAG GS DEV -FLAG
GS DEV +UP GS DEV +DOWN
}A
B
429 GPS IN
ILS ENERGIZE (A/P)
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. ONLY CONNECTIONS SUPPORTED BY THE AUTOPILOT ARE REQUIRED.
.
ALL "GAMA 429" CONFIGURATIONS OF THE GPS ARINC 429 OUTPUT PROVIDE DATA REQUIRED
4
BY THE AUTOPILOT FOR GPSS. THE "ARINC 429" CONFIGURATION CANNOT BE USED.
5
IFD5XX/4XX SETUP ITEMS:
MAIN SYSTEM CONFIG PAGE: DISCRETES ILS/GPS APR: APPROACH ONLY.
6. IF GPSS UNIT HAS AUTOMATIC LINE SPEED DETECTION, THE IFD OUTPUT SHOULD BE SET TO "LOW SPEED".
Figure D - 30: Autopilot Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN VERTICAL +FLAG
29
MAIN VERTICAL -FLAG
30
MAIN +UP
27
MAIN +DOWN
28
2
GPS ARINC 429 OUT A GPS ARINC 429 OUT B
46 47
GPS SELECT
13
ILS/GPS APPROACH
14
TO MAIN CDI
KAP100 (KC 190)
P1 P2
-
-
-
-
U
-
17
-
-
-
-
-
-
-
-
-
-
-
-
-
KAP 140 (KC 140)
P1 P2
22
-
23
-
24
-
25
-
-
31
-
12
-
9
-
10
-
-
-
-
KAP 150 KFC 150 (KC 19X)
P1 P2
-
-
-
-
U
-
17
-
-
21
-
Y
-
V
-
19
-
-
-
-
BENDIX KING
KFC 200 KFC 250 (KC 295) (KCP 299)
KFC 225 (KC 225)
P1 P2
P1 P2
-
-
23
-
-
-
24
-
-
C
25
-
-
A
26
-
C
-
-
14
D
-
-
15
M
-
-
12
K
-
-
52
-
-
46
-
-
-
47
-
KFC 300 (KCP 320)
KFC 275 KFC 325 (KCP 220)
AUTOPILOT
J1 J2TP P1
P2
P3
-
30
48
-
-
31
49
-
- LAT DEV FLAG + - LAT DEV FLAG -
2
-
3
-
- LAT DEV +LT
1
-
2
-
- LAT DEV +RT
-
24
-
27
- GS DEV FLAG +
-
25
-
10
- GS DEV FLAG -
3
-
4
-
-
11
- GS DEV +UP
-
28
- GS DEV + DOWN
-
-
-
-
48 429 GPS IN A
-
-
-
-
49 429 GPS IN B
-
-
-
26
-
-
-
-
-
34
-
-
-
-
- GPS SELECT (GND=GPS)
B
-
7
-
B
-
AA
-
7
-
-
29
22
-
- ILS ENERGIZE (A/P IN)
.
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
ALL GAMA 429 CONFIGURATIONS OF THE GPS ARINC 429 OUTPUT PROVIDE DATA REQUIRED BY AUTOPILOT FOR GPSS. THE ARINC 429 CONFIGURATION CANNOT BE USED.
32. SETUP ITEMS: MAIN SYSTEM CONFIG PAGE: GPS SELECT: PROMPT (KAP 140 AND KFC 225) AUTO (FOR ALL EXCEPT KAP 140 AND KFC 225)
4. IF AN EFIS IS INSTALLED, NONE OF THE CONNECTIONS SHOWN ARE REQUIRED. THESE AUTOPILOT SIGNALS ARE PROVIDED BY THE EFIS SYSTEM.
5. IF GPSS UNIT HAS AUTOMATIC LINE SPEED DETECTION, THE IFD OUTPUT SHOULD BE SET TO "LOW SPEED".
Figure D - 31: Bendix/King Autopilot Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN VERTICAL +FLAG
29
MAIN VERTICAL -FLAG
30
MAIN +UP
27
MAIN +DOWN
28
3
ILS/GPS APPROACH
14
TO MAIN CDI
CENTURY
CENTURY I
CENTURY II CENTURY III CENTURY IV CENTURY 21
CENTURY 31/41
CENTURY 2000
CENTURY TRIDEN
CD92
CD34
CD34 CD58
CD66
CD194
CD191
CD191
CD191
AUTOPILOT
-
-
-
-
-
2
-
-
-
-
-
3
13
B
B
-
32
4
14
A
A
-
31
5
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
B
45
-
-
-
-
A
46
-
-
-
-
-
44 2
1
7
7
7
LAT DEV FLAG +
8
8
8
LAT DEV FLAG -
6
6
6
LAT DEV +LT
5
5
5
LAT DEV +RT
2
2
2
GS DEV FLAG +
1
1
1
GS DEV FLAG -
4
4
4
GS DEV +UP
3
3
3
GS DEV + DOWN
9
9
9
LOC SWITCHING IN
.
Figure D - 32: Century Autopilot Interconnect Page 1 of 2
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
ILS/GPS APPROACH
14
2
1N4444 OR EQUIV
CD66 44
CENTURY IV
AUTOPILOT
LOC SWITCHING IN
IFD5XX/4XX
P1001
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
VLOC ANNUNCIATE
1
CD278
1 2 3
CENTURY AK
1081 GPSS
CONVERTER
429 IN HI 429 IN LO SHIELD
8
NAV SELECTED
4
4
429 IN SPEED SELECT
5
429 IN SPEED SELECT
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2 THE CENTURY IV REQUIRES THAT AN ISOLATION DIODE BE INSTALLED ON THE LOC SWITCHING INPUT AS SHOWN.
3. SETUP ITEMS, MAIN SYSTEM CONFIG PAGE: GPS SELECT: AUTO
4 INSTALL JUMPER AS REQUIRED TO SET AK 1081 ARINC 429 INPUT SPEED TO MATCH IFD5XX/4XX OUTPUT SETTING. REFER TO MANUFACTURER'S DOCUMENTATION FOR ADDITIONAL DETAILS.
Page 2 of 2
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN LATERAL +FLAG
23
MAIN LATERAL -FLAG
24
MAIN +LEFT
21
MAIN +RIGHT
22
MAIN VERTICAL +FLAG
29
MAIN VERTICAL -FLAG
30
MAIN +UP
27
MAIN +DOWN
28
3
GPS ARINC 429 OUT A GPS ARINC 429 OUT B
46 47
GPS ANNUNCIATE
2
ILS/GPS APPROACH
14
TO MAIN CDI
5
S-TEC/Cobham
AUTOPILOT
System Twenty
System Thirty System 40
System 50
System 55
System 55X
System 60-
System 60-1 System 60 PSS
2/65
P1
P1
P1
P1
P1 P2
P1 P2
0109
0110
0109 0110
-
-
-
-
13
-
13
-
24
-
24
-
NAV FLAG +
-
-
-
-
14
-
14
-
6
-
6
-
NAV FLAG -
9
9
14
14
31
-
31
-
23
10
10
13
13
30
-
30
-
21
-
23
-
L / R +LT
-
21
-
L / R +RT
-
-
-
-
-
1
-
1
-
77
-
77 GS FLAG +
-
-
-
-
-
2
-
2
-
58
-
58 GS FLAG -
-
-
-
-
-
18
-
18
-
46
-
46 GS +UP
-
-
-
-
-
19
-
19
-
45
-
45 GS + DOWN
-
-
-
-
-
-
-
36
-
-
-
-
-
-
-
-
37
-
-
-
-
429 GPS IN A
-
-
-
429 GPS IN B
-
-
-
-
-
-
-
38
-
42
42
26
26
49
-
49
-
-
-
-
-
-
32
-
32
-
16
-
-
-
GPS STEERING
-
-
-
GPS TRACK GAIN
-
16
-
LOC SWITCH
.
STEC ST-901 GPSS 3 CONVERTER
IFD5XX/4XX
P1001
J3
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
VLOC ANNUNCIATE
1
8 9
22
6
S-TEC ST-901
GPSS CONVERTER
ARINC DATA IN A ARINC DATA IN B
GPS OVERRIDE
STEC ST-901 GPSS CONVERTER 7
IFD5XX/4XX
P1001
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
VLOC ANNUNCIATE
1
GPSS (RELAXED)
NO GPSS (ENERGIZED)
(TO OTHER SYSTEM VLOC ANNUNCIATE SIGNAL)
J3
8 9
(AIRCRAFT POWER)
S-TEC ST-901
GPSS CONVERTER
ARINC DATA IN A ARINC DATA IN B
Figure D - 33: S-Tec Autopilot Interconnect Sheet 1 of 2
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IFD5XX/4XX Installation Manual
GPS ANNUNCIATE
IFD5XX/4XX
P1001
GPS ANNUNCIATE
2
(TO OTHER SYSTEM) (AIRCRAFT POWER)
S-TEC AUTOPILOT
GPSS STEERING
GPS TRACK GAIN
VLOC ANNUNCIATE
IFD5XX/4XX
P1001
VLOC ANNUNICATE
1
(TO OTHER SYSTEM) (AIRCRAFT POWER)
S-TEC AUTOPILOT ST-901 GPSS CONVERTER
J3
22
GPS OVERRRIDE
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. RESERVED 3 FOR CONVERTERS 01278-( ) S/N 600A AND ABOVE. 4 INSTALL JUMPER AS REQUIRED TO SET AK 1081 ARINC 429 INPUT SPEED TO MATCH IFD540 OUTPUT SETTING. REFER TO MANUFACTURER'S DOCUMENTATION FOR ADDITIONAL DETAILS. 5 IF THE GPS ANNUNCIATE SIGNAL IS ONLY USED BY THE AUTOPILOT, THIS MAY BE CONNECTED DIRECTLY. 6 IF THE VLOC ANNUNCIATE SIGNAL IS ONLY USED BY THE AUTOPILOT, THIS MAY BE CONNECTED DIRECTLY. 7 FOR CONVERTERS 01278-( ) 599 AND BELOW.
Sheet 2 of 2
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
MAIN LATERAL +LT OUT
21
MAIN LATERAL +RT OUT
22
MAIN VERTICAL +UP OUT
27
MAIN VERTICAL +DOWN OUT
28
MAIN LATERAL +FLAG OUT
23
MAIN LATERAL -FLAG OUT
24
MAIN VERTICAL +FLAG OUT
29
MAIN VERTICAL -FLAG OUT
30
2
MAIN LATERAL SUPERFLAG
17
OUT
MAIN VERTICAL SUPERFLAG
18
OUT
ILS/GPS APPROACH
14
TO MAIN CDI
APC 65/65B/65C/6 5E/65F/65H/65
J
J1 J3
-
54
-
53
-
41
-
44
-
4
-
1
-
12
-
9
-
4
N/C
1
-
12
N/C
9
35
-
COLLINS
FGC-65( ) FYD-65
APC 65A APC 65G
J1 J3
J1 J3
-
54
-
54
-
53
-
53
-
41
-
41
-
44
-
44
-
4
-
-
-
1
-
-
-
12
-
-
-
9
-
-
-
4
-
4
1
-
-
12
-
12
9
-
35
-
35
-
.
AUTOPILOT
VOR/LOC DEV +LT VOR/LOC DEV +RT GS DEV +UP GS DEV +DOWN NAV LL FLAG+ NAV LL FLAGGS LL FLAG+ GS LL FLAG-
2
NAV HL FLAG NAV LL FLAGGS HL FLAG GS LL FLAGLOC FREQ GND
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2 CONNECT EITHER THE LOW-LEVEL FLAGS OR THE SUPERFLAGS. DO NOT CONNECT BOTH SETS OF FLAGS IN A PARTICULAR INSTALLATION
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Figure D - 34: Collins Autopilot Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX #1 P1001
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
GPS ARINC 429 IN 1A
48
2
GPS ARINC 429 IN 1B
49
IFD5XX/4XX #1
GPS ARINC 429 IN 1A
48
2
GPS ARINC 429 IN 1B
49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
NAV SYSTEM 1
NAV SYSTEM 2
Bendix/King KFC 400 KCP420
P4201 P4202
ARINC 429
FLIGHT CONTROL SYSTEM
X
LNAV 1 RECEIVER A
X
LNAV 1 RECEIVER B
D
AFCS 429 GENERAL A
KK
AFCS 429 GENERAL B
J
ROLL STEERING STRAP
W
LNAV 2 RECEIVER A
F
LNAV 2 RECEIVER B
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2 IF THE GPS ARINC 429 IN PORT 1 IS ALREADY BEING USED, GPS ARINC PORT MAY BE USED. 3. LOWER CASE LETTERS SHOWN UNDERLINED. 4. REFER TO MANUFACTURERS' DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION.
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Figure D - 35: Bendix King KFC400 Autopilot Interconnect
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STACO INDICATOR CONNECTION 4
IFD5XX/4XX
P1001
VLOC ANNUNCIATE
1
GPS ANNUNCIATE
2
STACO INDICATOR
P1
VLOC
P1
2
3
N/C
9
6
11
12
GPS
LAMP VOLTAGE FROM DIMMER CIRCUIT
VIVISUN INDICATOR CONNECTION 5
IFD5XX/4XX
P1001
VLOC ANNUNCIATE
1
GPS ANNUNCIATE
2
VIVISUN INDICATOR
P1
VLOC
P1
C
B
G
D
A
GPS
LAMP VOLTAGE FROM DIMMER CIRCUIT
VIVISUN INDICATOR/SWITCH CONNECTION 6
IFD5XX/4XX
P1001
VLOC ANNUNCIATE
1
GPS ANNUNCIATE
2
CDI SOURCE SELECT
73
VIVISUN INDICATOR
P1
VLOC
P1
C
B
G
D
A
GPS
1
3
LAMP VOLTAGE FROM DIMMER CIRCUIT
Figure D - 36: External Navigation Source and GPS Annunciators Interconnect Page 1 of 2
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IFD5XX/4XX Installation Manual
IFD540
P1001
VLOC ANNUNCIATE
1
GPS ANNUNCIATE
2
WAYPOINT ANNUNCIATE
3
TERMINAL ANNUNCIATE
4
APPROACH ANNUNCIATE
5
MESSAGE ANNUNCIATE
6
OBS ANNUNCIATE
7
INTEGRITY ANNUNCIATE
9
OBS MODE SELECT
71
CDI SOURCE SELECT
73
7
9
MD41-14xx GPS ACU
7
-
8
-
2
8
4
3
6
9
3
10
-
24
1
20
-
12
-
-
8
2
2 VLOC ANN
1
1 GPS ANN
8
8 WPT ANN
3
3 TERM ANN
9
9 APR ANN
10
10 MSG ANN
24
24 OBS ANN
20
20 INTG ANN
12
12 OBS OMDE SELECT
4
- CDI SOURCE SELECT
NOTES:
1. ALL WIRES TO BE 24 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. IF NAVIAGATION ANNUNCIATORS IS REQUIRED, INDICATORS ON THIS PAGE ARE SUITABLE TO MEET THE ANNUNCIATION REQUIREMENT.
3. THE PREFERRED ANNUNCIATION IS VLOC/GPS, ALTHOUGH NAV/GPS WILL BE ACCEPTABLE.
4. STACO SWITCH INDICATOR P/N 992561-1241762200 (14V SYSTEMS) AND P/N 992561-1241862200 (28V SYSTEMS) SHOWN.
5. VIVISUN INDICATOR P/N 95-40-17-B6-AW724 (28V SYSTEMS) SHOWN. INDICATOR MAY BE CONVERTED TO 14V OPERATION BY REPLACING 28V LAMPS WITH 14V LAMPS P/N 14-113.
6. VIVISUN INDICATOR WITH MOMENTARY SWITCH P/N 95-45-11-B6-AW724 (28V SYSTEMS) SHOWN. INDICATOR MAY BE CONVERTED TO 14V OPERATION BY REPLACING 28V LAMPS WITH 14V LAMPS P/N 14-113.
7. THESE UNITS ALSO PROVIDE NAVIGATION SOURCE SELECTION ANNUNCIATION. MIDCONTINENT ANNUNCIATION CONTROL UNITS FOR BOTH 14V AND 28V SYSTEMS SHOWN. THIS DIAGRAM IS PROVIDED TO SHOW INTERCONNECTION BETWEEN IFD540 AND ACU ONLY. REFER TO MID-CONTINENT INSTALLATION MANUAL FOR ADDITIONAL INSTALLATION INFORMATION.
8. CDI SOURCE SELECTION AND ANNUNCIATION IS DONE WITH EXTERNAL RELAYS. REFER TO MID-CONTINENT INSTALLATION MANUAL FOR ADDITIONAL INSTALLATION INFORMATION.
9
5VDC VERSIONS: 146XA(5V) OR 147XA(5V).
10. ANNUNCIATOR PART NUMBER 146X HORIZONTAL ORIENTATION. PART NUMBER 147XA ARE VERTICAL ORIENTATION
Page 2 of 2
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IFD5XX/4XX
P1001
TIME MARK OUT
16
CDI SOURCE SELECT
73
OBS MODE SELECT
71
COM REMOTE RECALL
74
2
REMOTE CDI SWITCH (OPTIONAL) REMOTE OBS MODE SWITCH (OPTIONAL) REMOTE COM RECALL SWITCH (OPTIONAL)
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. TIME MARK OUT (P1001-16) OUTPUTS A 1 MILISECOND WIDE PULSE ONCE PER SECOND. 3. COM REMOTE RECALL (P1001-74) INPUT MAY BE USED TO SCROLL THROUGH A LIST OF PRESET COM FREQUENCIES.
Figure D - 37: Switch Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
GPS ARINC 429 OUT A 46 GPS ARINC 429 OUT B 47
GPS ARINC 429 IN 1A 48 GPS ARINC 429 IN 1B 49
P1006
VOR/ILS 429 OUT A 24
4 VOR/ILS 429 OUT B 23
P421 GARMIN GAD 42 3
1
GPS ARINC 429 IN A
2
GPS ARINC 429 IN B
13 GPS ARINC 429 OUT A 14 GPS ARINC 429 OUT B
3
NAV ARINC 429 IN A
4
NAV ARINC 429 IN B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. SEE GARMIN GAD 42 INSTALLATION MANUAL FOR COMPLETE PIN-OUT AND INTERCONNECTION INFORMATION. GAD42 MUST BE CONFIGURED USING STRAPS ON THE UNIT.
44.
NOT APPLICABLE FOR IFD IFD 510/545/410
Figure D - 38: Garmin GAD 42 Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
P1001
GPS 429 IN A 48 GPS 429 IN B 49
RS-232 OUT 56
TIME MARK OUT+ 16
GPS 429 OUT A 46 GPS 429 OUT B 47
P1006
7 VOR/ILS 429 OUT A
24
VOR/ILS 429 OUT B 23
GDU 620 PFD/MFD P6202
3
ARINC 429 OUT 1A
20 ARINC 429 OUT 1B
12 RS-232 IN 3 46 RS-232 GND 3
40 TIME MARK IN 1A
N/C
41 TIME MARK IN 1B
6
ARINC 429 IN 3A
23 ARINC 429 IN 3B
7
ARINC 429 IN 4A
24 ARINC 429 IN 4B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
3. REFER TO THE MANUFACTURER'S DOCUMENTATION FOR COMPLETE PIN-OUT AND INTERCONNECT INFORMATION. PIN-OUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
4. FOR PROPER SETUP TO INTERFACE WITH THE G600. REFER TO THE G600 INSTALLATION MANUAL. APPENDIX E (P/N 190-00601-06).
6. FOR OTHER CONNECTION OPTIONS REFER TO THE G600 INSTALLATION MANUAL.
7 .
NOT APPLICABLE FOR IFD 510/545/410
Figure D - 39: Garmin G600 Interconnect
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IFD 5XX/4XX #1 P1006
VOR/ILS ARINC 429 OUT A
24
6
VOR/ILS ARINC 429 OUT B
23
P1001
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
5
ARINC 429 RX A ARINC 429 RX B
48 49
IFD 5XX/4XX #2 P1001
5
ARINC 429 RX A ARINC 429 RX B
48 49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
P1006
6
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
IFD5XX/4XX Installation Manual
AVIDYNE 700-00006-XXX ENTEGRA EXP5000
J732
4
ARINC 429 RX CHL 2 A
3
ARINC 429 RX CHL 2 B
5
SHIELD GND
41
ARINC 429 RX CHL 1 A
40
ARINC 429 RX CHL 1 B
44
SHIELD GND
22
ARINC 429 TX CHL 0 A
21
ARINC 429 TX CHL 0 B
25
SHIELD GND
43
ARINC 429 RX CHL 4 A
42
ARINC 429 RX CHL 4 B
64
SHIELD GND
7
ARINC 429 RX CHL 3 A
6
ARINC 429 RX CHL 3 B
10
SHIELD GND
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE.
3. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED.
4. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION.
IF THE GPS ARINC 429 IN 1 PORT (P1001-48 AND -49) IS ALREADY USED FOR ANOTHER PURPOSE, THE GPS ARINC 429 5 IN 2 PORT (P1001-50 AND -51) MAY BE CONNECTED INSTEAD.
6 NOT APPLICABLE FOR IFD510/545/410
Figure D - 40: Avidyne Entegra Interconnect
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IFD5XX/4XX
GPS 429 TX GPS 429 TX
P1001
46 47
IFD5XX/4XX Installation Manual
EX500
P2 5/(48) 25/(68)
AVIDYNE
EX600
P2 5/(48) 25/(68)
EX5000
P2 5/(48) 25/(68)
MFD
GPS 429 RX GPS 429 RX
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE. 3. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 4. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION.
Figure D - 41: Avidyne EX500/600/5000 Interconnect
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IFD5XX/4XX Installation Manual
IFD 5XX/4XX #1 P1006
7
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
P1001
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
5
ARINC 429 RX A ARINC 429 RX B
48 49
ASPEN EFD1000
P1
18
429 VLOC RX2A
19
429 VLOC RX2B
16
429 GPS RX1A
17
429 GPS RX1B
26
EFD429 TX1A
27
EFD429 TX1B
IFD 5XX/4XX #2 P1001
5
ARINC 429 RX A ARINC 429 RX B
48 49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
P1006
7
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
20
429 GPS RX3A
21
429 GPS RX3B
22
VLOC RX4A
23
VLOC RX4B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE.
3. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED.
4. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION.
5 IF THE GPS ARINC 429 IN 1 PORT (P1001-48 AND -49) IS ALREADY USED FOR ANOTHER PURPOSE, THE GPS ARINC 429 IN 2 PORT (P1001-50 AND -51) MAY BE CONNECTED INSTEAD.
6. REFER TO MANUFACTURER'S INSTALL MANUAL FOR AIRDATA CONNECTION. ASPEN EFD1000 S/W 2.X OR LATER WILL TRANSMIT AIRDATA ON THE ARINC 429 TRANSMIT.
7 NOT APPLICABLE FOR IFD510/545/410
Figure D - 42: Aspen EFD1000 Interconnect (without ACU)
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IFD5XX/4XX Installation Manual
IFD 5XX/4XX #1 P1006
6
VOR/ILS ARINC 429 OUT A
24
VOR/ILS ARINC 429 OUT B
23
P1001
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
ARINC 429 RX A
48
ARINC 429 RX B
49
ASPEN EFD1000
P1
16
429 GPS RX1A
17
429 GPS RX1B
IFD 5XX/4XX #2 P1001
ARINC 429 RX A
48
ARINC 429 RX B
49
GPS ARINC 429 OUT A
46
GPS ARINC 429 OUT B
47
P1006
VOR/ILS ARINC 429 OUT A
24
6
VOR/ILS ARINC 429 OUT B
23
20
429 GPS RX3A
21
429 GPS RX3B
22
429 VLOC RX4A
23
429 VLOC RX4B
18
ACU RX2A
19
ACU RX2B
26
429 RX1A
27
429 RX1B
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
ASPEN ACU/ACU 2
P3
14
429 RX1B
1
429 RX1A
15
429 TX1B
2
429 TX1A
4
429 TX2A
5
429 TX2B
P1
1
429 RX2A
2
429 RX2B
2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE.
BACKSHELL OR USE CARD-EDGE
3. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED.
4. IF THE GPS ARINC 429 IN 1 PORT (P1001 -48 AND -49) IS ALREADY USED FOR ANOTHER PURPOSE, THE GPS ARINC 429 IN 2 PORT (P1001-50 AND -51) MAY BE CONNECTED INSTEAD.
5. THE ACU AND ACU2 TRANSMITS DIFFERENT ARINC 429 LABELS. REFER TO MANUFACTURER'S INSTALL MANUAL FOR DIFFERENCES BETWEEN THE ACU AND ACU2.
6 NOT APPLICABLE FOR IFD510/545/410
Figure D - 43: Aspen EFD1000 Interconnect (with ACU)
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
WEIGHT ON WHEELS
4
P1001
8
AVIDYNE AXP340 Primary
5
AVIDYNE AXP322
Primary 19
Trigg Avionics TRANSPONDER
TT31
Primary
5
SQUAT SWITCH IN
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. 4 IF THE AIRCRAFT HAS AN EXISTING WEIGHT ON WHEELS OUTPUT, DO NOT CONNECT.
IFD5XX/4XX
RS232 OUTPUT 2
4
RS232 INPUT 2
P1001
58 59
5
AVIDYNE AXP340 Secondary
3 -
5
AVIDYNE AXP322 25-PIN
5 7
TRANSPONDER
RS232 INPUT RS232 OUTPUT
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. 4 IF RS-232 PORT 2 IS NOT AVAILABLE, USE ANY OTHER AVAILABLE PORT. 5 ADS-B OUTPUT REQUIRES A SEPARATE INSTALLATION APPROVAL. 6. PILOT REQUIRED TO MANUALLY SWITCH FROM "ON" TO "ALT" AFTER TAKEOFF.
Figure D - 44: Transponder Interconnect
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IFD5XX/4XX Installation Manual
IFD5XX/4XX
4 RS232 OUTPUT 2
P1001
58
ELT
GPS RS232 INPUT
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. 4 IF RS-232 PORT 2 IS NOT AVAILABLE, USE ANY OTHER AVAILABLE PORT.
Figure D - 45: ELT Interconnect
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IFD5XX/4XX Installation Manual
IFD 5XX/4XX P1001
9
6
ARINC 429 IN A ARINC 429 IN B
48 49
AVIDYNE MLB100
P1
27
TIS 429 TX 1A
8
TIS 429 TX 1B
7
RS232 TX 2
58
34
RS232 GPS RX
32
GND
8
RS232 TX 1 RS232 RX 1
56 57
24
FIS DISPLAY RX
5
FIS DISPLAY TX
23
DISPLAY GND
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. AT IFD5XX/4XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE. 3. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 4. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. 5. IF RS232 OR ARINC429 PORTS ARE UNAVAILABLE, USE ANY OTHER AVAILABLE PORT. 6. IF SW VERSION 10.1.1, 10.1.2, OR 10.1.3 IS INSTALLED CONFIGURE ARINC 429 PORT FOR MLB Traffic, Port Speed: High 7. CONFIGURE GPS RS232 PORT FOR ADS-B+(G) 8. IF SW VERSION 10.2 OR LATER IS INSTALLED CONFIGURE DISPLAY RS232 PORT FOR SkyTrax100. 9. TRAFFIC DATA IS COMBINED WITH WEATHER OVER RS232 WITH SW VERSION 10.2 OR LATER. ARINC 429 CONNECTION IS NOT REQUIRED.
Figure D - 46: Skytrax100B (formerly MLB100) ADS-B IN Receiver Interconnect
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IFD5XX/4XX Installation Manual
IFD 5XX #1 P1050
ARINC 429 OUT 2 A
42
ARINC 429 OUT 2 B
43
3
ARINC 453 IN A ARINC 453 IN B
40 41
Bendix/King ART/RDR 2000
Antenna/Receiver
P5001
Transmitter
2
Control 1 ARINC 429 IN A
3
Control 1 ARINC 429 IN B
4
Control 2 ARINC 429 IN A
5
Control 2 ARINC 429 IN B
42 43
ARINC 453 OUT A ARINC 453 OUT B
3
31
RT#1 ON/OFF IN
32
RT#2 ON/OFF IN
NOTES:
1. ALL WIRES TO BE 22 AWG MINIMUM UNLESS OTHERWISE SPECIFIED.
2. IN DUAL IFDXXX INSTALLATIONS RADAR INPUT MUST BE CONNECTED TO THE UNIT WITH CHASSIS ID CONFIGURED FOR IFD #1. IFD4XX UNITS DO NOT SUPPORT ARINC 453 INPUT, BUT CAN DISPLAY RADAR DATA SHARED OVER CrossSync.
3. ARINC 453 DATA BUS: BOTH SHIELDS GROUNDED TO CONNECTOR SHELL AT ART/RDR 2000; OUTER SHIELD GROUNDED ONLY AT IFD5XX UNIT END. WIRE TO BE QUADRAX, NON-PVC JACKET, KPN: 024-00064-0000.
4. AT IFD5XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
5. ALL SHIELD GROUND CONNECTIONS SHOWN FOR THE ART/RDR 2000 ARE TO BE CONNECTED TO THE UNIT BACKSHELL GROUND.
6. THE IFD545.550 HAVE RADAR STABILIZATION, GO TO THE RADAR SETUP PAGE AND SELECT STABILIZATION ON.
7. SET THE IFD ARINC 429 #2 OUT TO ARINC 743A.
8. THESE ARE THE ELECTRICAL CONNECTIONS BETWEEN THE AVIDYNE IFD AND THE BENDIX / KING RDR2000 SYSTEM R/T UNITS. ALL OTHER WIRING IS AT THE DISCRETION OF THE INSTALLER.
Figure D - 47: RDR2000 Interconnect
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NOTES:
1. ALL WIRES TO BE 24 AWG MINIMUM UNLESS OTHERWISE SPECIFIED.
2. ALL GROUND CONNECTIONS SHOWN FOR THE GTX335 ARE TO BE CONNECTED TO SHIELD BLOCK GROUND.
3. AT IFDXXX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
4. IFDXXX SERIAL PORTS (RS232 AND ARINC 429) OTHER THAN THE ONES SHOWN ABOVE MAY BE SUBSTITUTED WITH APPROPRIATE UNIT SOFTWARE CONFIGURATION. Figure D - 48: GTX 335 Interconnect
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IFDXXX P1001
GPS RS232 OUT 1 56 GPS RS232 IN 1 57
7
ARINC 429 IN 1A 48 ARINC 429 IN 1B 49
4
TAWS AUDIO P1050
ACTIVE OUT 15
IFD5XX/4XX Installation Manual
Single IFDXXX Series
P3252
11
Garmin GTX 345
RS422 A (-)
7
P3251
30
RS232 IN 2
51
RS232 GND 2
5
ARINC 429 OUT A
6
ARINC 429 OUT B
37
AUDIO INHIBIT 4
IFDXXX #1 P1001
GPS RS232 OUT 1
56
GPS RS232 IN 1
57
7
ARINC 429 IN 1A
48
ARINC 429 IN 1B
49
Dual IFDXXX Series P3252
Garmin GTX 345
11
RS422 A (-)
7
P3251
30
RS232 IN 2
51
RS232 GND 2
5
ARINC 429 OUT A
6
ARINC 429 OUT B
IFDXXX #2
ARINC 429 IN 1A ARINC 429 IN 1B
7
GPS RS232 OUT 1 GPS RS232 IN 1
P1001
48 49
56 57
4
TAWS AUDIO P1050
ACTIVE OUT
15
29
RS232 IN 3
50
RS232 GND 3
37
AUDIO INHIBIT 4
Figure D - 49: GTX 345 Interconnect
(see below for notes)
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NOTES:
1. ALL WIRES TO BE 24 AWG MINIMUM UNLESS OTHERWISE SPECIFIED.
2. ALL GROUND CONNECTIONS SHOWN FOR THE GTX345 ARE TO BE CONNECTED TO SHIELD BLOCK GROUND.
3. AT IFD5XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
4. AUDIO INHIBIT MAY BE USED TO INHIBIT GTX-345 TIS-B ALERTS DURING IFD4XX/IFD5XX FLTA AURAL ANNUNCIATIONS. THIS DOES NOT AFFECT THE APPROVAL OF THE TIS-B FUNCTIONS OF THE GTX 345. GTX345 AUDIO INHIBIT MAY BE DRIVEN BY IFD#1 OR IFD#2 IN DUAL IFDXXX INSTALLATIONS. IFD4XX UNITS DO NOT DRIVE AUDIO INHIBIT. IN IFD4XX UNITS SIMULTAINEOUS TIS-B AND FLTA AURAL ANNUNCIATIONS ARE POSSIBLE (ADDRESSED IN AFMS).
5. IFDXXX SERIAL PORTS (RS232 AND ARINC 429) OTHER THAN THE ONES SHOWN ABOVE MAY BE SUBSTITUTED WITH APPROPRIATE UNIT SOFTWARE CONFIGURATION.
6. IFD4XX/IFD5XX FLTA FEATURE MUST BE DISABLED IF INSTALLED IN AIRCRAFT WITH APPROVED TAWS/EGPWS. THIS IS ACCOMPLISHED BY SELECTING "Yes" FOR THE "External TAWS" OPTION IN THE CONFIG TAB OF MAINTENANCE MODE.
7. CONFIGURE SELECTED POTS WITH THE FOLLOWING SETTINGS: · If the GTX 345 has an internal GPS receiver, the RS 232 position output connection and configuration setup is not required · IFDXXX RS232 output setting: ADS-B+ (G2).... GTX 345 RS 232 input setting: ADS-B+ FMT 2 · IFDXXX RS232 input setting: Capstone HS Wx .... GTX 345 RS 422 output setting: Optimized Legacy ADS-B · IFDXXX ARINC429 receive setting: GDL 88 Traffic at High Speed.... GTX 345 ARINC429 transmit setting: Traffic · Minimum Software Versions Required: IFD XXX v10.2.1 or higher....GTX 345 v2.05 or higher
Figure D -49: GTX 345 Interconnect (con't)
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IFD5XX/4XX Installation Manual
Single IFDXXX Series to GTX 330 ES
IFDXXX P1001
GPS RS232 OUT 2
58
P3301
Garmin GTX 330 ES
22
RS232 IN #1
DISCRETE OUT
11
ARINC 429 IN 1A
48
ARINC 429 IN 1B
49
P1050
5
TAWS/HTAWS AUDIO ACTIVE OUT
15
46
TIS CONNECT SELECT
30
ARINC 429 OUT 2A
28
ARINC 429 OUT 2B
47
AUDIO MUTE SELECT
5
IFDXXX #1
GPS RS232 OUT 2
P1001
58
Dual IFDXXX Series to GTX 330 ES
P3301
22
Garmin GTX 330 ES
RS232 IN #1
DISCRETE OUT
11
ARINC 429 IN 1A
48
ARINC 429 IN 1B
49
46
TIS CONNECT SELECT
30
ARINC 429 OUT 2A
28
ARINC 429 OUT 2B
IFDXXX #2 P1001
ARINC 429 IN 1A
48
ARINC 429 IN 1B
49
GPS RS232 OUT 2
58
24
RS232 IN #2
DISCRETE OUT
5
TAWS/HTAWS AUDIO ACTIVE OUT
NOTES:
11
P1050
15
47
AUDIO MUTE SELECT
5
1. ALL WIRES TO BE 24 AWG MINIMUM UNLESS OTHERWISE SPECIFIED.
2. ALL GROUND CONNECTIONS SHOWN FOR THE GTX 330 ES ARE TO BE CONNECTED TO SHIELD BLOCK GROUND.
3. AT IFDXXX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
4. IFDXXX SERIAL PORTS (RS232 AND ARINC 429) OTHER THAN THE ONES SHOWN ABOVE MAY BE SUBSTITUTED WITH APPROPRIATE UNIT SOFTWARE CONFIGURATION.
5. AUDIO INHIBIT MAY BE USED TO INHIBIT GTX330ES TIS ALERTS DURING IFD4XX/IFD5XX FLTA AURAL ANNUNCIATIONS. THIS DOES NOT AFFECT THE APPROVAL OF THE TIS FUNCTIONS OF THE GTX 330ES. AUDIO INHIBIT MAY BE DRIVEN BY IFD#1 OR IFD#2 IN DUAL IFDXXX INSTALLATIONS. IFD4XX UNITS DO NOT DRIVE AUDIO INHIBIT. IN IFD4XX UNITS SIMULTAINEOUS TIS-B AND FLTA AURAL ANNUNCIATIONS ARE POSSIBLE (ADDRESSED IN AFMS).
6. GTX 330 MUST BE "ES" ENABLED.
7. IFD4XX/IFD5XX FLTA FEATURE MUST BE DISABLED IF INSTALLED IN AIRCRAFT WITH APPROVED TAWS/EGPWS. THIS IS ACCOMPLISHED BY SELECTING "Yes" FOR THE "External TAWS" OPTION IN THE CONFIG TAB OF MAINTENANCE MODE.
Figure D - 50: GTX 330ES Interconnect
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AXP322 TRANSPONDER
25-PIN
RS232 OUTPUT
7
RS232 INPUT
5
SQUAT SWITCH IN
19
EXTERNAL STBY
17
SUPPRESSION IO
18
EXTERNAL IDENT
20
AIRCRAFT POWER
15
20 AWG
POWER ON
13
GROUND
1
GROUND
14
20 AWG 20 AWG
ANTENNA
IFD5XX/4XX Installation Manual
4
AVIDYNE IFD5XX/4XX
P1001 59 58 8
AVIDYNE DISPLAY
RS232 INPUT RS232 OUTPUT WOW Discrete
MUTUAL SUPPRESSION BUS
(OPTIONAL)
(OPTIONAL)
XPDR
3A
11-33VDC
CIRCUIT BREAKER
TO EXISTING ANTENNA
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. 4 IF RS-232 PORT 2 IS NOT AVAILABLE, USE ANY OTHER AVAILABLE PORT.
Figure D - 51: Avidyne AXP322 Interconnect
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IFDXXX
P1001
RS-232 INPUT 59
RS-232 OUTPUT 58
WOW Discrete
8
IFD5XX/4XX Installation Manual
POWER IN
1P
1T
2T
2P
1T
2T
3P
1T
2T
1T
4P
2T
Four poles Two throws
4PDT
POWER IN
25 PIN
AXP322 #1
15 AIRCRAFT POWER
13 POWER ON
1
GROUND
14 GROUND
7
RS-232 OUTPUT
5
RS-232 INPUT
19 SQUAT SWITCH IN
17 EXTERNAL STBY
25 PIN
AXP322 #2
7
RS-232 OUTPUT
5
RS-232 INPUT
19 SQUAT SWITCH IN
17 EXTERNAL STBY
15 AIRCRAFT POWER
13 POWER ON
1
GROUND
14 GROUND
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PIN-OUT AND INTERCONNECT INFORMATION. 4. IF RS-232 PORT 2 IS NOT AVAILABLE, USE ANY OTHER AVAILABLE PORT. 5. EACH TRANSPONDER MUST BE CONFIGURED. 6. CONFIGURE AXP322 WOW SELECTION TO AVIDYNE.
Figure D - 52: Avidyne Dual AXP322 Interconnect
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IFD5XX/4XX Installation Manual
FreeFlight FDL-978-RX J-1
RS232 TX 2 OUTPUT 33
RS232 RX 1 INPUT
4
REMOTE ON 32
2
RS232 RX 4 INPUT 25
GND
9
DISPLAY GPS
ENCODER
45 AVIDYNE DISPLAY
AVIDYNE
IFD5XX/4XX
P1001 55
4 5
RS232 (RX 4) INPUT
56
RS232 (TX1) OUTPUT
ENCODER
TO EXISTING ANTENNA
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. REFER TO MANUFACTURER'S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. 4 IF RS-232 PORT 2 IS NOT AVAILABLE, USE ANY OTHER AVAILABLE PORT. 5 SET IFD DISPLAY INPUT PORT TO CAPSTONE TRAFFIC & WX LOW SPEED (9600 BAUD) FOR S/W 10.2.0, CAPSTONE HS TRAFFIC & WX HI SPEED (38,400 BAUD) FOR S/W 10.2.1 AND LATER, GPS OUTPUT PORT TO ADS-B+(G) LOW SPEED (9,600 BAUD)
Figure D - 53: FreeFlight FDL 978RX Interconnect
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IFD5XX/4XX Installation Manual
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IFD5XX/4XX Installation Manual
P1001
GPS RS232 OUT 1
56
WX RS232 IN 1
57
TIME MARK
ARINC 429 IN 1A ARINC 429 IN 1B
4
TAWS AUDIO ACTIVE OUT
16
48 49
P1050
15
P881
26 34 45
RS232 IN 2 RS422 OUT 2A (-) RS232 GND 2
22
TIME MARK 1A
10
ARINC 429 OUT A
29
ARINC 429 OUT B
37
AUDIO INHIBIT #1 4
P1001
GPS RS232 OUT 1
56
WX RS232 IN 1
57
7
TIME MARK OUT
16
ARINC 429 IN 1A
48
ARINC 429 IN 1B
49
P1001
ARINC 429 IN 1A
48
ARINC 429 IN 1B
49
7
TIME MARK OUT
16
GPS RS232 OUT 1
56
WX RS232 IN 1
57
4
TAWS AUDIO ACTIVE OUT
P1050
15
P881
26 34 45
22
10 29
RS232 IN 2 RS422 OUT 2A (-) RS232 GND 2
TIME MARK 1A
ARINC 429 OUT A ARINC 429 OUT B
7
28
TIME MARK 2A
21
RS232 IN 5
56
RS422 OUT 1A (-)
40
RS232 GND 5
37
AUDIO INHIBIT #1 4
NOTES:
1. ALL WIRES TO BE 24 AWG MINIMUM UNLESS OTHERWISE SPECIFIED.
2. ALL GROUND CONNECTIONS SHOWN FOR THE GDL88 ARE TO BE CONNECTED TO SHIELD BLOCK GROUND.
3. AT IFD5XX UNIT, TERMINATE SHIELD GROUNDS TO THE CONNECTOR BACKSHELL OR USE CARD-EDGE CONNECTOR TO TERMINATE SHIELD GROUNDS TO BACK PLATE THE SHIELD LEADS MUST BE LESS THAN 3.0 INCHES. CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICLE. AUDIO INHIBIT MAY BE USED TO INHIBIT GDL88 ITS-B ALERTS DURING IFD4XX/IFD5XX FLTA AURAL ANNUNCIATIONS. THIS DOES NOT AFFECT THE APPROVAL OF THE TIS-B FUNCTIONS OF THE GDL88. GDL88 AUDIO INHIBIT MAY BE DRIVEN BY THE IFD#1 OR IFD#2 IN DUAL IFDXXX INSTALLATIONS. IFD4XX UNITS DO NOT DRIVE AUDIO INHIBIT. IN IFD4XX UNITS SIMULTAINEOUS TIS-B AND FLTA AURAL ANNUNCIATIONS ARE POSSIBLE (ADDRESSED IN AFMS).
5. IFDXXX SERIAL PORTS (RS232 AND ARINC 429) OTHER THAN THE ONES SHOWN ABOVE MAY BE SUBSTITUTED WITH APPROPRIATE UNIT SOFTWARE CONFIGURATION.
6. IFD4XX/IFD5XX FLTA FEATURE MUST BE DISABLED IF INSTALLED IN AIRCRAFT WITH APPROVED TAWS/EGPWS. THIS IS ACCOMPLISHED BY SELECTING "YES" FOR THE "EXTERNAL TAWS" OPTION IN THE CONFIG TAB OF MAINTENANCE MODE.
7. CONFIGURE SELECTED PORTS WITH THE FOLLOWING SETTINGS; If the GDL 88 has an internal GPS receiver, the RS 232 position output connection and configuration setup is not required IFDXXX RS 232 output setting: ADS-B+ (G2)....GDL88 RS 232 input setting: ADS-B Format 2 #1 and/or #2 as appropriate IFDXXX RS 232 input setting: Capstone HS Wx .... GDL 88 RS 422 input/output setting: Optimized Legacy ADS-B IFDXXX ARINC 429 receive setting: GDL88 Traffic at High Speed....GDL88 ARINC 429 transmit setting: Traffic Out at High Speed Minimum Software Versions Required: IFD XXX v10.2.1 or higher....GDL 88 v3.33 or higher
600-00299-000
Figure D - 54: GDL 88 Interconnect
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IFD5XX/4XX Installation Manual
Figure D - 55: Avidyne AXP340 Interconnect
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XMD076
WEATHER RS-232 TX WEATHER RS-232 RX
37 Pin
22 4
AUDIO LH HIGH
21
AUDIO LH LOW
2
AUDIO RH HIGH
20
AUDIO RH LOW
1
POWER ENABLE
18
POWER INPUT
19
POWER GND
37
14 28 VDC in
IFD5XX/4XX Installation Manual
AUDIO PANEL Connections To Be determined
by Installer
IFD P1001
59
RS-232 INPUT
58
RS-232 OUTPUT
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. IFD NEEDS SOFTWARE 10.2.3.1 OR HIGHER. 3. IFD WILL NOT CONTROL AUDIO FUNCTIONS. 4. WEATHER DISPLAY IS 115, 200 BAUD.
Figure D - 56: XMD076 Interconnect
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GDU 700/1060 PFD
P4
NAV ARINC 429 IN A
7
B 27
P3
TIME MARK IN 1A
30
TIME MARK IN 1B
31
RS-232 IN
4
RS-232 GND
25
P4
GPS ARINC 249 IN A
5
B
25
GPS ARINC 429 OUT A
53
B
73
IFD5XX/4XX Installation Manual
P1006
IFD #1
24
VOR/ILS 429 OUT A
23
VOR/ILS 429 OUT B
P1001
16 -
TIME MARK OUT + TIME MARK OUT -
3
56 GND
RS-232 OUT GROUND
46
GPS 429 OUT A
47
GPS 429 OUT B
48
GPS 429 IN A
49
GPS 429 IN B
P4
NAV ARINC 429 IN A 8 B 28
P3
TIME MARK IN 2A 28 TIME MARK IN 2B 29
RS-232 IN 6 RES-232 GND 26
P4
GPS ARINC 429 IN A 6 B 26
P1006
IFD #2
24
VOR/ILS 429 OUT A
23
VOR/ILS 429 OUT B
P1001
16 -
3 TIME MARK OUT +
TIME MARK OUT -
56 GND
RS-232 OUT GROUND
46
GPS 429 OUT A
47
GPS 429 OUT B
48
GPS 429 IN A
49
GPS 429 IN B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED
3
THE TIME MARK B CONNECTION MUST BE LEFT UNCONNECTED FOR THE INSTALLATION
OF IFD SERIES UNITS. A SINGLE CONDUCTOR SHILDED WIRE MAY BE USED FOR THE
TIME MARK IN THIS CASE
4. SHOWN ARE CONNECTIONS TO THE IFD's, ALL OTHER WIRING IS AT THE DESCRETION OF THE INSTALLER.
Figure D - 57: Single GDU700/1060 PFD Interconnect
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GDU 700/1060 PFD #1
P4
NAV ARINC 429 IN A
7
B 27
P3
TIME MARK IN 1A 30 TIME MARK IN 1B 31
RS-232 IN
4
RS-232 GND 25
P4
GPS ARINC 249 IN A
5
B
25
GPS ARINC 429 OUT A
53
B
73
P3
TIME MARK IN 2A 28 TIME MARK IN 2B 29
RS-232 IN 6 RES-232 GND 26
P4
GPS ARINC 429 IN A 6 B 26
IFD5XX/4XX Installation Manual
P1006
IFD #1
24
VOR/ILS 429 OUT A
23
VOR/ILS 429 OUT B
P1001
16 -
3 TIME MARK OUT +
TIME MARK OUT -
56 GND
RS-232 OUT GROUND
46
GPS 429 OUT A
47
GPS 429 OUT B
48
GPS 429 IN A
49
GPS 429 IN B
N/C
GDU 700/1060 PFD #2
P3
TIME MARK IN 1A 30 TIME MARK IN 1B 31
RS-232 IN
4
RS-232 GND 25
P4
NAV ARINC 429 IN A
5
B 25
P3
TIME MARK IN 2A 28 TIME MARK IN 2B 29
RS-232 IN 6 RES-232 GND 26
P4
GPS ARINC 249 IN A 6 B 26
GPS ARINC 429 OUT A 53 B 73
P4
NAV ARINC 429 IN A 7 B 27
IFD #2
P1001
16 -
3 TIME MARK OUT +
TIME MARK OUT -
56 GND
RS-232 OUT GROUND
46
GPS 429 OUT A
47
GPS 429 OUT B
48
GPS 429 IN A
49
GPS 429 IN B
P1006
24
VOR/ILS 429 OUT A
23
VOR/ILS 429 OUT B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED
THE TIME MARK B CONNECTION MUST BE LEFT UNCONNECTED FOR THE INSTALLATION
3
OF IFD SERIES UNITS. A SINGLE CONDUCTOR SHILDED WIRE MAY BE USED FOR THE
TIME MARK IN THIS CASE
4.
SHOWN ARE CONNECTIONS TO THE IFD's, ALL OTHER WIRING IS AT THE DESCRETION
OF THE INSTALLER.
Figure D - 58: Dual GDU700/1060 PFD Interconnect
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G5 (HSI)
2P51
RS-232 RX
4
SIGNAL GROUND
6
IFD5XX/4XX Installation Manual
IFD P1001
56 GND
RS-232 OUT RS-232 GND
GAD 29/29B
P292
ARINC 429 RX 1A (GPS)
23
ARINC 429 RX 1B (GPS)
11
ARINC 429 TX 1A (EFIS/AIR DATA)
24
ARINC 429 TX 1B (EFIS/AIR DATA)
12
3
ARINC 429 RX 2A (NAV)
22
ARINC 429 RX 2B (NAV)
10
46
ARINC 429 OUT A
47
ARINC 429 OUT B
48
ARINC 429 IN A
49
ARINC 429 IN B
P1006
24
23
ARINC 429 OUT A
ARINC 429 OUT B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. IFD NEEDS SOFTWARE 10.2.3.1 OR HIGHER.
3
GAD29B INSTALLED WHEN INTERFACING TO A THIRD PARTY AUTOPILOT SEE GAD29B INTERFACE TO THIRD PARTY AUTOPILOT INTERCONNECT
DIAGRAMS FOR FURTHER INFORMATION.
IFD Config Page MAIN ARINC 429 CONFIG Page
Config Option IN (x)
OUT VNAV
MAIN RS-232 CONFIG Page
VOR/LOC/GS ARINC 429 CONFIG Page
Configuration Setting Speed = Low
Data = EFIS / Airdata Speed = Low
Data = GAMA 429 ENABLED
Input = OFF Output = MapMX (WAAS GPS)
AVIATION (non WAAS GPS)
RX = Low TX = Low VOR/ILS 1
Figure D - 59: Garmin G5 EHSI Interconnect
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IFD5XX/4XX Installation Manual
G5 (ATTITUDE INDICATOR)
1P51
RS-232 RX 1
4
SIGNAL GROUND
6
IFD
P1001
56 GND
RS-232 OUT RS-232 GND
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED.
IFD Config Page
Configuration Setting
Input = OFF
MAIN RS-232 CONFIG PAGE Output = MapMX (WAAS GPS)
AVIATION (non WAAS GPS)
Figure D - 60: Garmin G5 EADI Interconnect
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G5 (ATTITUDE INDICATOR)
1P51
RS-232 RX 1
4
SIGNAL GROUND
6
IFD5XX/4XX Installation Manual
IFD P1001
56 GND
RS-232 OUT RS-232 GND
G5 (HSI)
2P51
RS-232 RX
4
SIGNAL GROUND
6
GAD 29/29B
P292
ARINC 429 RX 1A (GPS)
23
ARINC 429 RX 1B (GPS)
11
ARINC 429 TX 1A (EFIS/AIR DATA)
24
ARINC 429 TX 1B (EFIS/AIR DATA)
12
3
ARINC 429 RX 2A (NAV)
22
ARINC 429 RX 2B (NAV)
10
46
ARINC 429 OUT A
47
ARINC 429 OUT B
48
ARINC 429 IN A
49
ARINC 429 IN B
P1006
24
ARINC 429 OUT A
23
ARINC 429 OUT B
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. IFD NEEDS SOFTWARE 10.2.3.1 OR HIGHER.
GAD29B INSTALLED WHEN INTERFACING TO A THIRD PARTY AUTOPILOT
3
SEE GAD29B INTERFACE TO THIRD PARTY AUTOPILOT INTERCONNECT
DIAGRAMS FOR FURTHER INFORMATION.
IFD Config Page MAIN ARINC 429 CONFIG Page
Config Option IN OUT
VNAV
Configuration Setting Speed = Low Garmin GAD42 Speed = Low
Data = GAMA 429
ENABLED
MAIN RS-232 CONFIG Page
Input = OFF Output = MapMX (WAAS GPS)
Aviation (Non WAAS GPS)
VOR/LOC/GS ARINC 429 CONFIG Page
SPEED SDI
Figure D - 61: Garmin G5 EFIS Interconnect
RX = Low TX = Low VOR/ILS 1
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NGT9000R
RS-232 RX1 RS-232 TX1
W OW/SQ UA T/SP EED SWITCH DISC 3 IN
RS-422 A (-)
J1/P1
61 62
29
53
IFD5XX/4XX Installation Manual
IFD P1001
58 RS-232 OUT 2 59 RS-232 IN 2
8
Wow
57 RS232 in 1
RS-232 RX3
60
GROUND
16
ENCODER
4
DCM SDA
17
DCM SCL
18
DCM 3.3V
19
DCM GND
20
+14 VDC or +28 VDC in 1
1
+14 VDC or +28 VDC in 2
2
14 or 28 V RETURN 1
3
14 or 28 V RETURN 2
4
POWER IN
CONFIGURATION MODULE
NOTES:
1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED.
2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED
3. CONFIGURE NGT9000R WOW INPUT TO OPEN IN AIR.
4
REFER TO THE INSTALLATION MANUAL OF THE ALTITUDE ENCODER FOR PINOUT AND FORMAT SETTINGS.
5. CONFIGURE NGT9000R RS-232 OUT BAUD TO 115,200.
6. CONFIGURE IFD RS-232 INPUT TO CAPSTONE TFC + Wx HIGH SPEED.
7. CONFIGURE THE IFD RS-232 OUTPUT/INPUT TO NGT9000R
Figure D - 62: NGT9000R Interconnect
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KT-74
Primary J1
7
5
IFD5XX/4XX Installation Manual
IFD P1001
56 RS-232 OUT
8
wow
11
POWER IN
12
9
SUPPRESSION IN/OUT
F
EXTERNAL IDENT
1
A
Secondary J2
3 1
SERIAL ENCODER
X X
Pinout dependent on
encoder Model
NOTES: 1. ALL WIRES TO BE 22 AWG OR GREATER UNLESS OTHERWISE NOTED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED. 3. SET SQUAT SWITCH SETTING TO LOW WHEN GROUND. 4. SET GPS POSITION SOURCE TO TRIG ADS-B AT 9600 BPS. 5. SET GPS CERTIFICATION TO LEVEL C. 6. SET GPS NACv TO 1 OR < 10m/SECOND. 7. SET THE IFD OUTPUT TO ADS-B (AVI). 8. PARALLEL ALTITUDE WIRING, NOT SHOWN, CAN BE USED IN PLACE OF SERIAL ALTITUDE.
Figure D - 63: KT-74 Interconnect
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IFD5XX P1050
GPS OUT 2 A
42
GPS OUT 2 B
43
IFD5XX/4XX Installation Manual
P1 TDR94 #1
49
GPS IN
50
GPS IN
P1 TDR94 #2
49
GPS IN
50
GPS IN
NOTES: 1. ALL WIRES TO BE 22 AWG MINIMUM UNLESS OTHERWISE SPECIFIED. 2. WIRE HARNESS OVERBRAID IS NOT SHOWN BUT MAY BE REQUIRED . 3. CONFIGURE IFD ARINC 2 OUT TO HIGH SPEED, ARINC 743A. 4. SHOWN IS THE CONNECTIONS TO THE IFD. ALL OTHER WIRING IS AT
THE DISCRETION OF THE INSTALLER.
Figure D - 64: TDR-94 Interconnect
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Appendix E: Troubleshooting Guide
Component IFD5XX/4XX
Trouble
The unit is not getting power to the main connector
Probable Cause The unit is not getting power.
The IFD5XX/4XX is not computing a position
The GPS Signal levels are very low
Wiring Antenna Wiring
Antenna shading
Interference
VHF Com is not transmitting
(Not Applicable for IFD510/545/410)
Wiring
The IFD5XX/4XX is not tuning the DME
(Not Applicable for IFD510/545/410)
Configuration Wiring DME
RS-232 Device is not communicating
Configuration
Wiring ARINC 429 is not communicating Configuration
Solution Check Circuit Breaker
Check wiring and unit seating in tray
Check Coaxial Cables
Verify antenna has a clear unobstructed view of the sky Check coaxial cable and connectors Check routing Verify the antenna is mounted on top of the aircraft Verify antenna is clear of hangars, buildings, etc. Verify another piece of aircraft equipment is not interfering with the GPS system Check the aircraft's PTT switch
Check Audio Panel (if installed) Check wiring Verify the IFD5XX/4XX is configured correctly. Checking wiring
Verify the DME is configured for the IFD5XX/4XX tuning type
Verify the IFD5XX/4XX is configured for the appropriate device. Check wiring and unit seating in tray Verify the IFD5XX/4XX is configured for the appropriate device.
Wiring
Check wiring and unit seating in tray
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Component IFD5XX/4XX
Trouble
Display appears excessively dim or off
Probable Cause
Configuration (configured for "night mode")
Solution
Check cockpit dimming rheostat position
Check Flight Mode settings on User Options page for Display and Bezel Brightness and source
Check power button on IFD
Check Mx Mode settings on Lighting page for proper setting
CMOS Battery Dead CAS Message
VHF Radio Slots displaying RedXs (Not Applicable for IFD510/545/410)
The 10-year life expectancy of the CMOS battery has been reached. This may result in longer GPS satellite acquisition times.
No power on the P1002 Connector
Chassis ID not set to 0 or 1
Return the IFD to Avidyne Service Center for battery replacement
Ensure all governing circuit breakers have power
Check and set as required the Chassis ID per section 7.3
Unit starts up in Maintenance Mode
USB fob installed at power up
IFD last shut down in Maintenance Mode
Unable to get out of Maintenance Mode or not sure how to
IFD to IFD Communication is not functional as indicated by either "CROSSYNC FAIL" CAS message or no data sharing observed between the IFDs
"Config Mismatch" CAS message on IFD5XX/4XX (dual IFD5XX/4XX only)
IFD is misconfigured
Wiring incorrect Configuration mismatch between the two IFD units
Ensure fob is not in the USB slot and reapply power to the IFD
Press the left or right side of the AUX page until the "DONE" Line Select Key is visible and press that LSK to force the IFD to restart into flight mode
Press the left or right side of the AUX page until the "DONE" Line Select Key is visible and press that LSK to force the IFD to restart into flight mode
Ensure RS-232 Channel 3 is set to CrossSync on each IFD
Ensure serial Channel 3 wiring is installed per Section 4.7
Power cycle the IFD units
Verify configuration on IFD5XX/4XX units
If problem persists, send IFD5XX/4XX log data to Avidyne Technical Support
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IFD5XX/4XX Installation Manual
Appendix F: Configuration Setup
In order to support the requirements of some validations of the AML STC, this section should be easily removable and inserted into the aircraft logs.
For those installations where an IFD5XX/4XX is replacing a GNS-530/W or GNS-430, please record the following parameters from the GNS-530/W or GNS-430/W setup pages before removing the unit (Note: this will need to be conducted for each GNS-530/W or GNS-430/W being replaced):
WAAS Enabled (530W or 430W with approved antenna)? Yes
No
N/A
2nd unit: Yes
No
530/W or 430/W Hardware Part Number and Revision Number (back of unit or aircraft logs) _______________/_______________
530/W or 430/W Software Part Number ("Main SW Version" on start up splash screen) __-________________/_______________
If multiple GNS-530/W or GNS-430/W were installed, describe the slot/location that this specific unit was removed from.
Cockpit Location of Unit(s) in Question
Description of location/slot in the cockpit (Include rough sketch if deemed helpful)
Measure the distance from the ground to the top of the GPS antenna to nearest tenth of a foot, as shown in the image below, and enter the value in the box below: (to the nearest 1/10th foot).
Measured Height of GPS Antenna
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Please list the other avionics that are installed in the aircraft (please be as specific as possible with make and models of the gear) and connected to the GNS-530/W or GNS-430/W. Enter "None" or "Don't Know" as required. The GNS530/W or GNS-430/W Setup pages will be captured on subsequent pages.
Traffic Datalink Lightning Sensor Autopilot Fuel Flow System Display(s) CDI(s) RMI(s) Transponder DME ADF Air Data IRU/INS Other Other Other
Identification of Devices Connected to the GNS-530/W or GNS-430/W
1st GNS 530/W or GNS 430/W
2nd GNS 530/W or GNS-430/W (if applicable)
Please list the other avionics that are installed in the aircraft and connected to the IFD5XX/4XX. Enter "None" or "Don't Know" as required. The IFD5XX/4XX Setup pages will be captured on subsequent pages.
Identification of Devices Connected to the IFD5XX/4XX at time of Install
1st IFD5XX/4XX
2nd IFD5XX/4XX (if applicable)
Traffic
Datalink
Lightning Sensor
Autopilot
Fuel Flow System
Display(s)
CDI(s)
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IFD5XX/4XX Installation Manual
GNS-530/W or GNS-430/W Maintenance Mode Entry:
GNS-530 configuration data is accessed from the GNS-530/W Maintenance Mode settings which is entered via holding ENTR button on 530/W bezel during power application.
GNS-530/W or GNS-430/W Page Navigation:
Use the inner right knob on the GNS-530/W to scroll through the maintenance mode pages. Each clockwise click of the knob selects the next page. On pages where selectable fields exist, a push of the right knob will produce a flashing cursor. The outer right knob moves through the fields on a page when there is a flashing cursor. Twist the inner right knob clockwise to see a list of choices. Use the inner right knob to scroll through the list of choices and press the "ENT" button to select the desired choice.
IFD5XX/4XX Maintenance Mode Entry:
IFD5XX/4XX configuration data is accessed via Mx Mode which is entered by starting the IFD with a USB Fob already installed or selecting the AUX page, SYS tab, ensuring that the "Select" LSK = Software, and then pressing the "Download Logs" LSK, followed by the "Confirm" LSK. These tables contain all the data that can be entered at time of installation to ensure the IFD5XX/4XX is properly configured. There are additional setup options that selectable by the pilot (Display Options on AUX Setup tab) that are not documented here.
IFD5XX/4XX Page Navigation:
To reach the IFD pages on which this data is to be entered, select the CONFIG tab in Maintenance Mode. Use the outer right knob to select the page each clockwise click of the outer right knob selects the next page in the list. Push the right knob in to generate a cursor and then use the outer right knob to select an individual field with the cursor. Then twist the inner right knob to scroll through the selectable options for that field and push in the right knob when done with each field selection.
For retrofit installations (those installations in which an IFD5XX/4XX is replacing a GNS-530/W or GNS-430/W), enter the data in the following tables/menu pages from the corresponding fields recorded below in the GNS-530/W or GNS430/W tables on the left side of each page. Repeat for each retrofit IFD5XX/4XX.
For new installations (those installations in which an IFD5XX is NOT replacing a GNS-530/W or GNS-430/W), select and record the appropriate settings for each configuration page per the descriptive material below each table.
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Garmin 530/W or 430/W - MAIN ARINC 429 CONFIG page
Speed
Data
IN 1
IN 2
OUT
SDI
VNAV (if present)
IFD5XX/4XX - Main ARINC 429 Config Page (1/12)
Speed
Data
In 1
In 2
Out
SDI
VNAV For new IFD5XX installations, see Section 7.5.2 for selections and descriptions
GNS-530/W or 430/W MAIN RS232 CONFIG Page
CHNL 1
Input
Output
CHNL 2
CHNL 3
CHNL 4
CHNL 5
IFD5XX/4XX - Main RS232 Config Page (2/12)
CHNL 1
Input
Output
CHNL 2
CHNL 3
CHNL 4
CHNL 5
CHNL 6
For new IFD5XX Installations, see Section 7.5.3 for selections and descriptions. IFD4XX do not have Channels 5 and 6.
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GNS-530/W or 430/W MAIN SYSTEM CONFIG Page (Fuel)
CONFIGURE Fuel
FUEL TYPE
IFD5XX/4XX Installation Manual
GNS-530/W or 430/W MAIN SYSTEM CONFIG Page (Terrain) [if present]
CONFIGURE
TERRAIN TYPE
TEST CARD?
Terrain
HW CONFIG
012-00296-
012-00401-
GNS-530/W or 430/W MAIN SYSTEM CONFIG Page (Discretes) [if present]
CONFIGURE Discretes
GPS SELECT
COM PRESETS
Note: Com Presets are always enabled on the IFD5XX/4XX
GNS-530/W or 430/W MAIN SYSTEM CONFIG Page (Airframe) [if present]
CONFIGURE Airframe
AIRFRAME
AIR/GROUND (if present)
Note: The Air/Ground selection is only present when helicopter is selected for the airframe and is a trigger to look for squat switch input. No equivalent in IFD5XX/4XX.
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IFD5XX/4XX Main System Config page (3/12)
Fuel Type
GPS Select
Airframe
Tail Number
External TAWS WOW Input (Helo) Checklists TIS-B Annunciation Joystick Input
Tail Number is a free text field and is used for JSUM.
IFD5XX/4XX Installation Manual
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GNS-530/W or 430/W MAIN INPUTS Page
OAT SAT TAT IAS TAS
HDG
W DIR
GPS SC
VLC SC
CDI
B ALT D ALT P ALT
L FF
R FF
W SPD
JOYSTICK WPT
T FF
T FOB
IFD5XX/4XX Installation Manual
IFD5XX/4XX MAIN INPUTS Page (4/12)
OAT SAT TAT IAS TAS
HDG
W DIR
GPS SC
VLC SC
CDI
B ALT D ALT P ALT
L FF
R FF
W SPD
T FF
T FOB
JOYSTICK WPT
Note: There is no data to enter on the IFD5XX/4XX from this page it is for diagnostics only
GNS-530/W or 430/W INSTRUMENT PANEL SELF TEST (For reference only)
CDI
FUEL CAPACITY
FLG VCDI
FUEL ONBOARD
VFLG
TO/FRM
FUEL FLOW
ANNUN
RMI
Set Fuel Flow?
OBS
DTK
No IFD5XX/4XX Equivalent Page
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GNS-530/W or 430/W MAIN LIGHTING Page
Display
Key
LIGHTING
SOURCE
RESP TIME / MIN
SLOPE / OFFSET
PHOTO TRANS % (if applicable)
PHOTO SLP / OFST (if applicable)
IFD5XX/4XX Installation Manual
IFD5XX/4XX MAIN LIGHTING Page (5/12)
Bezel
Display
Photo Response Time
Photo Slope
Photo Minimum
Photo Maximum
dimBus Transition %
dimBus Slope
dimBus Minimum
dimBus Maximum
dimBus Curve
Current
Lighting
Dimming Bus
Calibration
Bezel
dimBus Type
Display
dimBus Max Voltage
Mx Input
dimBus Min Voltage
See Section 7.5.6 for instructions on this page.
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GNS-530/W or 430/W DATE / TIME SETUP Page (No Need to Fill In For Reference Only)
UTC DATE
UTC TIME
IFD5XX/4XX Installation Manual
No IFD5XX/4XX Equivalent Page
GNS-530/W or 430/W MAIN DISCRETE I/O Page
GRAY CODE
DECODED ALTITUDE
EXTERNAL SWITCH STATE
RMT CDI
OBS
APR GPS
DISCRETE TOGGLE
OBS
TERM
ILS/GPS APR
INTEG
VLOC
MSG
WPT
Note: Check off the squares, as required, to match the solid squares on the GNS-530/430 unit these check that discretes are wired correctly.
IFD5XX/4XX MAIN DISCRETE I/O Page (6/12)
GRAY CODE
DECODED ALTITUDE
EXTERNAL SWITCH STATE
RMT CDI
RMT OBS
TER INHB
AUD INHB
RMT RCL
DISCRETE TOGGLES
APR
OBS
ILS/GPS APR
GPS
TERM
GPS SELECT
INTEG
VLOC
TER CAUT
MSG
WPT
TER INHB
TER N/A
TER WARN Note; ON or OFF will be Displayed
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GNS-530/W or 430/W MAIN CDI / OBS CONFIG Page
CDI
NAV TO-
FLAG FROM
LAT
VERT
SELECTED COURSE
CDI
OBI
V-
SOURCE FLAG
STATE
IFD5XX/4XX Installation Manual
IFD5XX/4XX MAIN CDI / OBS CONFIG Page (7/12)
CDI
NAV TO-
FLAG FROM
LAT
VERT
SELECTED COURSE
Ignore SEL CRS for GPS
Ignore SEL CRS for VLOC
CDI
OBI
V-
SOURCE FLAG
STATE
For new IFD5XX/4XX installations, see Section 7.5.8 for selections and descriptions.
GNS-530/W or 430/W COM SETUP Page (GNS-530W/430W Only)
FREQ
SQ 250
SPACING
SQ 833
SIDETN
MIC
STORE CALIBRATION?
PTT
XFR RX
TX
Note: The squares above do not need to be recorded they fill in when/if that function is activated.
No IFD5XX/4XX Equivalent Page
(Use the User Options tab to select 25 or 8.33 kHz spacing)
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IFD5XX/4XX Installation Manual
GNS-530/W or 430/W VOR/LOC/GS CDI Page
CDI NAV SPR TOFLAG FLAG FROM
LAT VERT SELECTED COURSE
DME CHANNEL MODE
GNS-530W or GNS-430W Only
IFD5XX/4XX VOR/LOC/GS CDI Page (8/12)
CDI NAV SPR TOFLAG FLAG FROM
LAT VERT SELECTED COURSE
DME CHANNEL MODE
For new IFD5XX/4XX installations, see Section 7.5.9 for selections and descriptions.
GNS-530/W or 430/W VOR/LOC/GS ARINC 429 CONFIG Page (GNS-530W/430W Only)
RX
TX
SPEED
SDI
DME MODE
IFD5XX/4XX VOR/LOC/GS ARINC 429 CONFIG Page (9/12)
SPEED
RX
TX
FORMAT
SDI
DME MODE
For new IFD5XX/4XX installations, see Section 7.5.10 for selections and descriptions.
GNS-530/W or 430/W GPS Vertical Offset (if present)
GPS Antenna Height Above Ground
IFD5XX/4XX GPS Antenna Setup Page (10/12)
GPS Antenna Height Above Ground
Antenna Type
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Note: Use the data recorded at the beginning of Appendix F to enter the Antenna Type field.
GNS-530/W or 430/W STORMSCOPE CONFIG Page (if configured for Stormscope)
STATUS:
MODE:
SW VERSION:
ANT MOUNT:
HDG FORMAT
HDG FLG SENSE
HDG FLAG
SYNC ANGLE
HDG STAB
SYNC REF
HDG VALID
Note: Squares should all be green if no issues.
IFD5XX/4XX Installation Manual
IFD5XX/4XX STORMSCOPE CONFIG Page (Software version 10.2 or higher)
Accessible via the TEST page, select GET DATA, scroll to Config, and record the jumpers installed and grounded
HEADING J3-1
INPUT
J3-2
OPEN OPEN
GND GND
HEADING
FLAG
J3-4
SENSE
ANTENNA J3-3
MOUNT
OPEN OPEN
GND GND
GNS-530/W or 430/W STORMSCOPE TEST Page (if configured for Stormscope)
MODE
STATUS
TRIGGER COUNT
HDG
IFD5XX/4XX STORMSCOPE TEST Page (Software version 10.2 or higher)
MODE
STATUS
TRIGGER COUNT
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HDG
IFD5XX/4XX Installation Manual
GNS-530/W or 430/W STORMSCOPE DATA DOWNLOAD Page (if configured for Stormscope)
SOFTWARE VERSIONS:
Model Main SW Ver Main Boot SW Ver DSP SW Ver
SOFTWARE VERSIONS:
Model Main SW Ver Main Boot SW Ver DSP SW Ver
IFD5XX/4XX STORMSCOPE DATA Page (Software version 10.2 or higher)
GNS-530/W or 430/W Traffic Config Page (if configured for Traffic)
ALT
LIM A (if 429 interface) LIM B (if 429 interface) HDG (if 429 interface)
BARO ALT
RAD ALT
TEST MODE?
(if 429 interface) (if 429 interface) (if 429 interface)
No IFD5XX/4XX Equivalent Page
Note: Traffic monitoring is accomplished after a 3 minute suppression period in-flight when any faults are announced. There should be no Red-X on the traffic thumbnail if configured on the Setup pages.
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Note: Check off the squares, as required, to match the solid squares on the GNS-530 unit.
IFD5XX/4XX Installation Manual
GNS-530/W or 430/W RYAN TCAD CONFIG Page (if configured for Ryan TCAD]
MODE
APPROACH MODE
HEIGHT
RANGE
GND/FLD ELEVATION
VOLUME
MUTE DURATION
VOICE ALERT
UNKNOWN DEVICE
STATUS MUTE
No IFD5XX/4XX Equivalent Page
Note: Use the presence of the traffic thumbnail and the Audio Volume Control page to control these parameters in the IFD5XX/4XX.
GNS-530/W or 430/W GAD 42 Config Page (if configured for an ARINC 429 input from GAD
42)
MAIN RMI/OBI
NAV RMI/OBI
SEL CRS DRIVE
DIST SERIAL
ROLL STEERING
REMOTE CRS SEL
TAS INPUT
GPS/NAV 429 L/H
HEADING 429 L/H
GAD SW VER:
STATUS:
No IFD5XX/4XX Equivalent Page
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Note: Manually strap the GAD42 or ensure stored configuration is not lost.
IFD5XX/4XX Installation Manual
The IFD5XX/4XX alerts in flight mode if the GAD42 reports a fault.
GNS-530/W or 430/W TAWS Audio Config Page 1 (if installed)
TAWS CONFIG
VOICE GENDER
VOLUME PLAY AUDIO
MSG
No IFD5XX/4XX Equivalent Page
(Use the User Options LSK and Volume Control LSK of the Audio Tab instead)
GNS-530/W or 430/W TAWS Audio Config Page 2 (if installed)
ALERT Reduced Terrain Clearance CAUT WARN ALERT Reduced Obstacle Clearance CAUT WARN ALERT Imminent Terrain Impact CAUT WARN ALERT Imminent Obstacle Impact CAUT WARN
No IFD5XX/4XX Equivalent Page (Use the User Options Tab instead)
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GNS-530/W or 430/W GDL Config Page (if installed)
ATTENUATION
MODEL (if displayed)
IFD5XX/4XX Installation Manual
IFD5XX/4XX GDL Config Page (if installed) (11/12)
ATTENUATION MODEL
QOS
GNS-530/W or 430/W DATALINK DIAGNOSTICS Page (if installed)
TERR
SAT 1
SAT 2
TUNER
No IFD5XX/4XX Equivalent Page
Note: Use the Datalink Status page on the AUX-SYS tab for datalink status data.
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IFD5XX/4XX Installation Manual
Notice:
SOFTWARE LICENSE: AVIDYNE CORPORATION ("AVIDYNE") IS WILLING TO LICENSE THIS SOFTWARE, AND RELATED MATERIALS (THE "SOFTWARE") ONLY ON THE CONDITION THAT THE USER AGREES TO THE TERMS OF THE PUBLISHED SOFTWARE LICENSE WHICH CAN BE ACCESSED VIA THIS WEB ADDRESS: HTTP://WWW.AVIDYNE.COM/SUPPORT/LICENSE.ASP
FCC APPROVAL AND CAUTIONS: THIS DEVICE COMPLIES WITH PART 15 OF THE FCC RULES. OPERATION IS SUBJECT TO THE CONDITION THAT THIS DEVICE DOES NOT CAUSE HARMFUL INTERFERENCE. THE MANUFACTURER IS NOT RESPONSIBLE FOR ANY RADIO OR TV INTERFERENCE CAUSED BY UNAUTHORIZED MODIFICATIONS TO THIS EQUIPMENT. SUCH MODIFICATIONS COULD VOID THE USER'S AUTHORITY TO OPERATE THE EQUPMENT.
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IFD5XX/4XX Installation Manual
®
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© Copyright 2014-2018 Avidyne Corporation
Rev: 17
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Avidyne 700-00182-XXX and 700-00179-XXX Integrated Flight Display
Instructions for Continued Airworthiness
As installed in ____________________________________
(Make and Model Airplane) Reg. No. ____________ S/N______________
AVIDYNE
CORPORATION
Avidyne Corporation 4 Middlesex Green, Suite 221
561 Virginia Road Concord MA 01742
Important Notice
With respect to the AML STC, the physical mounting of antennas are specifically excluded from the approval in
the case of installations on the pressure vessel of pressurized aircraft or composite aircraft unless approved data is listed in the Master Document List of
the STC.
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Document Revision History
Document Number AVIFD-315
Control Category
Revision Description
ECO
Date
00
Initial Release
ECO-13-199 08/30/13
01
AEG Comments
ECO-13-350 09/27/13
02
Update Part Numbers
ECO-13-405 01/20/14
03
Removing ADS-B
ECO-14-059 03/03/14
04
Added 700-00179-XXX
ECO-15-129 03/20/15
05
AEG Comments
ECO-15-169 04/22/15
06
FAA Comments
ECO-15-193 05/05/15
Update f or Release 10.2. Added
07
IFD410, IFD510, IFD545, IFD550, ARS troubleshooting instructions and IFD550
ECO-16-326 12/21/16
figure
08
Address AEG comments sections 2, 6, 7 ECO-17-013 01/18/17
09
Add additional configuration to table1, section 1.5
ECO-19-050 04/17/19
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Instructions for Continued Airworthiness
Table of Contents
1. Introduction............................................................................. 5
1.1 Applicability..............................................................................................................5 1.2 Definitions and Abbreviations ...................................................................................6 1.3 Precautions..............................................................................................................7 1.4 Units of Measure......................................................................................................7 1.5 Referenced Publications...........................................................................................7 1.6 Distribution...............................................................................................................7
2. Description.............................................................................. 8
2.1 Equipment Locations................................................................................................9
3. Control and Operation Information .................................... 11
3.1 Page Function Keys ...............................................................................................12 3.2 Line Select Keys ....................................................................................................12
4. Servicing Information .......................................................... 12 5. Maintenance Instructions .................................................... 13
5.1 Scheduled Maintenance .........................................................................................13 5.2 Recommended periodic scheduled servicing tasks .................................................13 5.3 Software Upgrade ..................................................................................................14
6. Troubleshooting Information .............................................. 15 7. Removal and Replacement Information ............................ 17
7.1 IFD5XX/IFD4XX Removal ......................................................................................17 7.2 IFD5XX/IFD4XX Installation ...................................................................................17 7.3 GPS Antenna Removal ..........................................................................................17 7.4 GPS Antenna Installation .......................................................................................17 7.5 Tray Removal.........................................................................................................18 7.6 Tray Installation......................................................................................................18 7.7 System Setup and Checkout ..................................................................................18
8. Application of Protective Treatments ................................ 19 9. Data ........................................................................................ 19 10. List of Special Tools ......................................................... 19
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11. For Commuter Category Aircraft ..................................... 19 12. Recommended Overhaul Periods ................................... 19 13. Airworthiness Limitations Section .................................. 19 14. Revision.............................................................................. 20 15. Assistance.......................................................................... 20 16. Implementation and Record Keeping ............................. 20
List of Figures
Figure 1: IFD5XX/IFD4XX Location - Single Engine .......................................................................... 9 Figure 2: IFD5XX/IFD4XX Location Multi Engine......................................................................... 10 Figure 3: IFD540/510 Unit .................................................................................................................. 11 Figure 4: IFD4XX Unit ......................................................................................................................... 11 Figure 5: IFD545/550 Unit .................................................................................................................. 11
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AVIFD-315 Revision: 09, Date: 04/17/19
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Instructions for Continued Airworthiness
1. Introduction
This document identifies the Instructions for Continued Airworthiness (ICA) for the modification of the aircraft listed in AVIFD-318 Integrated Flight Display STC Approved Model List by installation of an Avidyne 700-00182-XXX (IFD5XX) and/or 700-00179-XXX (IFD4XX) Integrated Flight Display.
This ICA satisfies the requirements of 14 CFR 23.1529.
Modification of an aircraft by this Supplemental Type Certificate obligates the aircraft operator to include the maintenance information provided by this document in the operator's Aircraft Maintenance Manual and the operator's Aircraft Scheduled Maintenance Program.
1.1 Applicability
This document applies to aircraft altered by the installation of the following equipment. Equipment should be installed using data listed in 700-00182-XXX/700-00179-XXX Integrated Flight Display Master Document List, document number AVIFD-306:
Table 1 IFD Part Number Variants
Part Number
Description
700-00179-010 700-00179-710 700-00179-110 700-00179-810 700-00179-000 700-00179-700 700-00179-100 700-00179-800 700-00182-010 700-00182-710 700-00182-110 700-00182-810 700-00182-000 700-00182-700 700-00182-001 700-00182-701
INTEGRATED FLIGHT DISPLAY, IFD410, BLACK BEZEL
INTEGRATED FLIGHT DISPLAY, IFD410, GREY BEZEL
INTEGRATED FLIGHT DISPLAY, IFD440, BLACK BEZEL
INTEGRATED FLIGHT DISPLAY, IFD540, GREY BEZEL
INTEGRATED FLIGHT DISPLAY, IFD510, BLACK BEZEL
INTEGRATED FLIGHT DISPLAY, IFD510, GREY BEZEL
INTEGRATED FLIGHT DISPLAY, IFD540, BLACK BEZEL
INTEGRATED FLIGHT DISPLAY, IFD540, BLACK BEZEL WITH VIDEO
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Part Number
700-00182-002
700-00182-100 700-00182-800 700-00182-101 700-00182-801 700-00182-102
700-00182-030 700-00182-730 700-00182-031 700-00182-731 700-00182-130 700-00182-830 700-00182-131 700-00182-831 700-00182-020 700-00182-720 700-00182-021 700-00182-721 700-00182-120 700-00182-820 700-00182-121 700-00182-821
Description
INTEGRATED FLIGHT DISPLAY, IFD540, BLACK BEZEL, 16W VHF
INTEGRATED FLIGHT DISPLAY, IFD540, GREY BEZEL
INTEGRATED FLIGHT DISPLAY, IFD540, GREY BEZEL WITH VIDEO
INTEGRATED FLIGHT DISPLAY, IFD540, GREY BEZEL, 16W VHF
INTEGRATED FLIGHT DISPLAY, IFD545, BLACK BEZEL
INTEGRATED FLIGHT DISPLAY, IFD545, BLACK BEZEL, WITH VIDEO
INTEGRATED FLIGHT DISPLAY, IFD545, GREY BEZEL
INTEGRATED FLIGHT DISPLAY, IFD545, GREY BEZEL, WITH VIDEO
INTEGRATED FLIGHT DISPLAY, IFD550, BLACK BEZEL
INTEGRATED FLIGHT DISPLAY, IFD550, BLACK BEZEL, WITH VIDEO
INTEGRATED FLIGHT DISPLAY, IFD545, GREY BEZEL
INTEGRATED FLIGHT DISPLAY, IFD550, GREY BEZEL, WITH VIDEO
1.2 Definitions and Abbreviations AML - Approved Model List ARS Attitude Reference Sensor ICA - Instructions for Continued Airworthiness IFD - Integrated Flight Display STC - Supplemental Type Certificate AMM Aircraft Maintenance Manual
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AVIFD-315 Revision: 09, Date: 04/17/19
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Instructions for Continued Airworthiness
1.3 Precautions This section is not applicable.
1.4 Units of Measure This section is not applicable.
1.5 Referenced Publications
Document Number 600-00299-000 600-00300-001 600-00304-000 89000039-010 89000041-008 600-00317-000 600-00318-000 600-00319-000
Title IFD5XX/IFD4XX Installation Manual
IFD5XX Series Pilot's Guide IFD4XX Series Pilot's Guide Bendix King AeroNav 900 and 910 Pilot's Guide Bendix King AeroNav 800 Pilot's Guide IFD550 and IFD545 Pilot's Guide
IFD510 Pilot's Guide IFD410 Pilot's Guide
1.6 Distribution
This Instruction for Continued Airworthiness is to be furnished with new production IFD systems and is to become part of the permanent aircraft records upon installation.
A current revision of this ICA shall be available on the Avidyne website at www.avidyne.com (Technical Publications in the Products section).
In the event of a service bulletin or other circumstances that require an update, Avidyne will notify the contact as listed on the owner registration.
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Instructions for Continued Airworthiness
2. Description
The IFD system is a panel mounted integrated system that provides navigation, communication, and multifunction display capability in one display. The IFD5XX/IFD4XX can display information from a wide variety of aircraft sensors. The IFD's are available in the following variations:
IFD540 AeroNav 900 IFD550 AeroNav 910 IFD545 -
IFD510 -
IFD440 AeroNav 800 IFD410 -
Baseline 5.7" Display unit with GPS/NAV/COM
Same as IFD540 but with integral attitude reference sensor ARS, add'l page button (SVS) Same as IFD540 but with integral attitude reference sensor ARS, add'l page button (SVS) without NAV/COM functions, GPS only, left knob removed Same as IFD540 but without NAV/COM functions, GPS only, left knob removed Baseline 4.8" Display unit with GPS/NAV/COM
Same as IFD440 but without NAV/COM functions, GPS only, left knob removed
The IFD410 and IFD440 can be a plug-and-play replacement for the Garmin GNS4XX series of NAV/COM/GPS units.
The IFD510, IFD545, IFD540 and IFD550 can be a plug-and-play replacement for the Garmin GNS5XX series of NAV/COM/GPS units.
When replacing a Garmin unit, follow the existing approved ICA, STC manual, or OEM instructions.
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Instructions for Continued Airworthiness
2.1 Equipment Locations
The installer should indicate on the outlines below the locations for the following items at the time of installation: IFD5XX/IFD4XX unit, wire harness location and routing, coaxial cables, and antennas. Use Figure 1 for single engine airplanes or Figure 2 for multi engine airplanes.
Figure 1: IFD5XX/IFD4XX Location - Single Engine
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Figure 2: IFD5XX/IFD4XX Location Multi Engine
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3. Control and Operation Information
The IFD5XX/IFD4XX System can be controlled using the button and knobs on the bezel of the unit. Alternately, some functions can be controlled using the touch-screen on the unit's display.
Figure 3: IFD540/510 Unit Figure 4: IFD4XX Unit
Figure 5: IFD545/550 Unit
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3.1 Page Function Keys
The 3 buttons along the bottom of the IFD bezel are called Page Function Keys. Each key is labeled by function:
· FMS (Flight Management System)
· Map (Moving Map) · AUX (Auxiliary Pages)
Each page has a number of associated tabs. Each Page Function key has a left and right rocker nature to it. Select the page of interest by pressing the middle of the Page Function Key and navigate through the available tabs by pressing the left or right.
3.2 Line Select Keys
Line Select Keys, typically abbreviated to LSK, are the buttons found along the left side of the bezel. A label, just inside the bezel adjacent to the physical LSK, indicates the function of the LSK. Pressing the LSK or the label either performs the labeled action or changes the state. For the cases where there is a list of selectable options, browse the list by repeatedly pressing the LSK or label.
4. Servicing Information
The 700-00182-XXX and 700-00179-XXX IFD can only be serviced by qualified and properly rated facility.
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Instructions for Continued Airworthiness
5. Maintenance Instructions
Other than the scheduled and periodic inspection tasks discussed below, maintenance of the Avidyne IFD5XX/IFD4XX is based on condition and function only; no other periodic maintenance is required.
5.1 Scheduled Maintenance
The following tasks may be required on the IFD5XX/IFD4XX: a. If the IFD5XX/IFD4XX is providing GPS position to the ELT, every 12 months verify the Emergency Locator Transmitter (ELT) is operating correctly per the ELT maintenance instructions.
5.2 Recommended periodic scheduled servicing tasks
There are no life limited components in the IFD5XX/4XX that require scheduled inspection or service. Perform the following inspections during annual/100 hour maintenance interval to establish airworthy condition and function. 1. During any maintenance activities involving the IFD System perform (i.e.
IFD removal, cable repair...) a post-installation check as described in Installation Manual, Integrated Flight Display Installation Manual 60000299-000.
2. Visually inspect (no magnification required) wire/bundle, coaxial cables, overbraid (if installed), and routing for evidence of damage, chafing, grounding, security, bonding, integrity of shields, and connector backshell condition.
3. Visually inspect (no magnification required) the mechanical installation for any defects or damage to the aircraft structure or to the IFD5XX/IFD4XX.
4. Visually inspect (no magnification required) the GPS, COM, NAV, and Glideslope antennas. Verify bonding of the antennas is no greater than 2.5 milliohm.
5. Verify that the bonding between the aircraft and each unit of the IFD system should have a resistance no greater than 2.5 milliohm as described in the Integrated Flight Display Installation Manual 600-00299-000.
6. Verify that all mandatory Service Alerts and/or Service Bulletins for the IFD System have been accomplished. (This can be done using the internet at www.avidyne.com).
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Instructions for Continued Airworthiness
5.3 Software Upgrade
The following procedures should be followed when performing optional or mandatory software change to the IFD System:
1. Acquire the software image and associated loading procedure from the manufacturer.
2. Verify the software part number configuration before and after maintenance is performed on the airborne equipment using the loading procedure instructions.
3. It is the responsibility of maintenance personnel to ensure the identified part is recorded in the necessary maintenance logs.
4. It is the maintenance personnel's responsibility to ensure that the software part identification has been logged. When new software is loaded into the unit, the correct software part number should be verified according to the instructions accompanying the software change before the unit is returned to service. Hardware versions are identified on the data label by brackets following the main part number.
5. Changes to software part number, version, and/or operational characteristics should be reflected in the Operator's Manual, Aircraft Flight Manual, Aircraft Flight Manual Supplement, and/or any other appropriate document.
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AVIFD-315 Revision: 09, Date: 04/17/19
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Instructions for Continued Airworthiness
6. Troubleshooting Information
Refer to the manufacturers' installation and user's manuals to assist in troubleshooting. The following items present common installation problems and recommended actions for the Avidyne IFD5XX/IFD4XX System.
Component GPS
Trouble
The IFD5XX/IFD4XX is not computing a position
The GPS Signal Levels drop when avionics are turned on.
The GPS signal levels are very low.
VHF Communication
VHF Communication transceiver is not transmitting
VHF Communication transceiver power is low
Probable Cause
Solution
Aircraft is not positioned in a
Move aircraft to a better location
location to receive GPS satellites
GPS Antenna System
Check Antenna coaxial cables for proper assembly
Check or replace the GPS antenna
Noise interference from other avionics
Turn off all avionics off, then turn on each piece one at time to isolate the interference to the
Antenna
Verify the GPS antenna is connected to the correct antenna
Repair or Replace antenna
Antenna shaded from satellites Move aircraft to a better location
Interference from avionics
Re-route GPS antenna system away from sources of interference.
Interference from a VHF Communication transmitter
Move GPS antenna away from the VHF Communication antenna or install a 1575.22 MHz notch filter.
The PTT input is not being grounded
Check PTT input to the IFD5XX/IFD4XX
VSWR too high Coaxial Cable
Check VSWR is less than 3:1 Repair or replace coaxial cable
Navigation Receiver
VHF Navigation Receiver not receiving VOR/LOC station
Antenna
Repair or Replace VHF Com antenna
VHF Navigation station not tuned Tune the IFD5XX/IFD4XX to the
correctly.
correct station
Antenna
Repair or Replace Antenna
Diplexer
Repair or Replace Diplexer
Coaxial Cables
Repair or Replace Cable
Attitude Reference System (ARS) (IFD545/550)
RMI pointer
The pitch ladder and horizon are replaced with Red X
RMI not displaying indicating
ARS Failure Wiring
Replace IFD Check wiring
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Component DME
ARINC device
RS-232 device
Battery Replacement
Trouble correctly
IFD5XX/IFD4XX is not tuning the DME correctly
ARINC 429 is not receiving / transmitting data from the IFD5XX/IFD4XX
ARINC 429 is not receiving / transmitting data from the IFD5XX/IFD4XX
Battery Annunciation on IFD540/440
Probable Cause Desired RMI not selected VHF Navigation station not tuned correctly. IFD5XX/IFD4XX configuration Wiring VHF Navigation station not tuned correctly Wiring
IFD5XX/IFD4XX configuration
Wiring
IFD5XX/IFD4XX configuration
The IFD540/440 internal battery has failed
Solution
Select the IFD5XX/IFD4XX on the RMI
Tune the IFD5XX/IFD4XX to the correct station
Verify the IFD5XX/IFD4XX is configured for the correct DME
Check wiring
Tune the IFD5XX/IFD4XX to the correct station
Make sure wire harness is connected. Check the wire harness and repair or replace if needed.
Verify the IFD5XX/IFD4XX is configured for the ARINC device Verify the ARINC 429 device speed is set correctly on the IFD5XX/IFD4XX
Make sure wire harness is connected. Check the wire harness and repair or replace if needed.
Verify the IFD5XX/IFD4XX is configured for the RS-232 device Verify the RS-232 device speed is set correctly on the IFD5XX/IFD4XX
Contact Avidyne for Repair
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Instructions for Continued Airworthiness
7. Removal and Replacement Information
Removal and replacement instructions, including system set-up and installation verification, are contained in the Integrated Flight Display Installation Manual. Unit removal, installation, setup and checkout should be performed by an Avidyne Authorized Service Center. Caution: Prior to removing any piece of electronic equipment, aircraft power must be removed from the system.
7.1 IFD5XX/IFD4XX Removal
1. Insert a 3/32" hex wrench into the hole on the front panel on the IFD5XX/IFD4XX and engage locking screw.
2. Turn the locking screw counter-clockwise to loosen locking cam. Cam will move the unit out ¼" and disengage the electrical connectors.
3. Remove unit from tray. 7.2 IFD5XX/IFD4XX Installation
1. Slide the IFD5XX/IFD4XX unit into the tray. 2. Insert a 3/32" hex wrench into the hole on the front panel on the
IFD5XX/IFD4XX and engage locking screw. 3. Turn the locking screw clockwise to tighten the locking cam until the
unit is flush to the tray. 4. Perform post-installation verification per Section 7.7. 7.3 GPS Antenna Removal
1. Remove sealant from around the base of the antenna. 2. Disconnect coaxial cable 3. Remove fasteners from antenna 4. Lift antenna clear of fuselage 7.4 GPS Antenna Installation
1. Position antenna on aircraft 2. Attach antenna to fuselage with fasteners 3. Verify the GPS antenna is bonded to the airframe. With the coaxial
cable disconnected, the bond between the antenna base plate and the aircraft metallic skin must measure 2.5 milliohm 4. Seal any minor gaps between the antenna base plate or gasket and the aircraft skin with RTV silicone adhesive sealant 5. Connect GPS coaxial cable 6. Perform post-installation verification per Section 7.7.
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Instructions for Continued Airworthiness
7.5 Tray Removal 1. Remove IFD from Tray, See Section 7.1 2. Remove fasteners from Tray and Connectors 3. Remove tray from instrument panel
7.6 Tray Installation 1. Re-install fasteners in connectors and tray 2. Re-install IFD, see Section 7.2 3. Verify the tray is bonded to the airframe. The bond between the tray and the airframe must measure 2.5 milliohm 4. Perform post-installation verification per Section 7.7.
7.7 System Setup and Checkout
After any maintenance activity involving the IFD System, the postinstallation checkout should be performed. Verify the following functions of the IFD5XX/IFD4XX is operating correctly, reference the IFD5XX/IFD4XX Installation Manual and Pilot Guide as need.
The installation manual, Avidyne Document 600-00299-000 Rev. 10 (or later FAA approved revision), contains detail setup and testing information if needed.
7.7.1 VHF Communication Checkout Tune the VHF Communication Transceiver to an unused frequency, verify the IFD5XX/IFD4XX can receive and transmit on that frequency.
7.7.2 Navigation Checkout Verify the IFD5XX/IFD4XX GPS Navigation and VHF Navigation (if installed) is operating correctly including navigation source selection. If installed, verify the following is operating correctly: navigation displayed on a CDI/HSI, external annunciation, and audio output.
7.7.3 External Sensor Checkout The IFD5XX/IFD4XX can be connected to several different external sensors. Verify each sensor is operating correctly per the manufacturer's maintenance information.
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Instructions for Continued Airworthiness
8. Application of Protective Treatments
This section is not applicable.
9. Data
Reference the 700-00182-XXX and 700-00179-XXX STC Master Document List, Avidyne Document AVIFD-306, for installation data. The Installation Manual, Avidyne Document 600-00299-000 Rev. 10 (or later FAA approved revision), contains the wiring diagrams for the system. Also, reference FAA AC 43.13 as needed.
10. List of Special Tools No special tools are required for this installation.
11. For Commuter Category Aircraft This section is not applicable.
12. Recommended Overhaul Periods No overhaul periods are required for this installation.
13. Airworthiness Limitations Section There are no Airworthiness Limitations as defined in 14 CFR § 23, Appendix G. 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.
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14. Revision
Revisions to this document shall be coordinated through the Boston Aircraft Certification Office, the Kansas City AEG, and the STC holder. If you would like to be notified of future revisions to this manual please furnish the information listed below:
Name Address City, State, and ZIP Code Part Number of Manual Current Revision Status of the Manual E-mail address Phone Number
Please submit this information to: Avidyne Corporation 4 Middlesex Green, Suite 221 561 Virginia Road Concord MA 01742
15. Assistance
For questions or assistance regarding this ICA, contact Avidyne Corporation.
16. Implementation and Record Keeping
This ICA must be incorporated into applicable section for aircraft inspections, 91.409 for annual/100 hour inspections or 135.419 for FAA approved alternate inspections.
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EASA Installation Checklist IFD4XX and IFD5XX Series AML STC
AVIDYNE
CORPORATION
4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742
Document Number
AVIFD-484
Revision
Description
00
Initial Release
01
Software 10.2 revision
02
Wi-Fi Bluetooth update
Control Category ECO ECO-16-110 ECO-17-041 ECO-17-237
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IFD4XX and IFD5XX Series AML STC
Table of Contents
1. Purpose .................................................................................. 3 2. EASA Regulatory Compliance ............................................. 4 3. Installation Checklist Instructions ....................................... 5 4. Additional Requirements ...................................................... 6 5. Weight and Balance .............................................................. 7 6. Electrical Load Analysis ....................................................... 8
6.1 Aircraft with Existing Electrical Load Analysis ............................................................. 8 6.2 Aircraft without Existing Electrical Load Analysis ........................................................ 8 6.3 Electrical Load is Reduced Following Modification ..................................................... 9 6.4 Electrical Load is Increased Following Modification .................................................... 9 6.5 Performing an Electrical Load Analysis by Measurement ......................................... 10
7. Post Installation Verification .............................................. 13
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
1. Purpose
This installation checklist is intended to document the installation of the Avidyne IFD4XX and IFD5XX series Integrated Flight Display.
For installations on aircraft registered in countries under EASA oversight, this installation checklist controls and limits the IFD4XX and IFD5XX Installation Manual, part number 60000299-000. In some cases, European rules provided more explicit requirements; this checklist limits the applicability of certain configurations in the IFD4XX and IFD5XX Installation Manual to those permitted for EASA-registered aircraft. Reference the IFD4XX and IFD5XX Installation Manual for instructions on the installation of the IFD4XX series and IFD5XX series Integrated Flight Display. For installations on aircraft registered in the United States, this installation checklist supplements the IFD4XX and IFD5XX Installation Manual, part number 600-00299-000 but is not approved data under FAA STC SA00343BO.
NOTE: The IFD4XX/IFD5XX STC does not cover installation of antennas or drilling of holes through pressurized vessels or composite structures. Separate approval will be needed if those changes are made while installing the IFD4XX and IFD5XX.
NOTE: When installing the IFD4XX and IFD5XX under this STC, separate approval is required if the operational capabilities of the aircraft are to be changed (i.e., change from VFR-only to IFR)
NOTE: EASA aircraft operating rules have priority over any conflicting data or instructions in the IFD4XX and IFD5XX Installation Manual, part number 600-00299-000 except when specifically addressed in this Installation Checklist.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
2. EASA Regulatory Compliance
When the data required by this installation checklist is completed, it can be used by the DOA/applicant to show compliance to the following EASA Certification Specifications:
EASA CS 23 23.1301(c)
Compliance Data
Installation Checklist
23.1301(d)
Installation Checklist
23.1309(c)(1) 23.1351(a) 23.1353(h) 23.1357(d) 23.1365(c)
Installation Checklist
Installation Checklist
Installation Checklist
Installation Checklist
Installation Checklist
23.1365(d)
Installation Checklist
23.1431(b) 23.1519
Installation Checklist
Installation Checklist
Notes
This regulation is met if the equipment installed by this STC is installed according to the data in this document (AVIFD-484) and the IFD 5XX/4XX Installation Manual.
This regulation is met upon successful completion of the System Configuration/Checkout in Section 7 of the IFD 5XX/4XX Installation Manual and the Post-Installation Verification in Section 7 of this document.
This regulation is met upon successful completion of the ELA required by Section 6.
This regulation is met upon successful completion of the ELA required by Section 6.
This regulation is met upon successful completion of the ELA required by Section 6.
This regulation is met upon successful verification of the circuit breaker checks in Section 7.
This regulation is met upon successful verification of the wiring checks in Section 7.
For 23.1365, although the overall rule is the same, individual subparts of the rule are lettered in a different order between the EASA CS and U.S. FARs:
· CS 23.1365(c) maps to 14 CFR 23.1365(d)
This regulation is met if the equipment installed by this STC is installed according to the data in this document and the IFD 5XX/4XX Installation Manual. For 23.1365, although the overall rule is the same, individual subparts of the rule are lettered in a different order between the EASA CS and U.S. FARs:
· CS 23.1365(d) maps to 14 CFR 23.1365(e
This regulation is met upon successful completion of the interference checks in Section 7.
This regulation is met upon successful completion of the weight and balance required by Section 5.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
3. Installation Checklist Instructions
Follow the instructions below for completion of the airworthiness approval after installation of the IFD4XX Series and IFD5XX Series under this STC.
1. Fill out Appendix F of 600-00299-000, IFD 5XX/4XX Installation Manual to document the installation. Section 4 of this document contains configuration setting requirements for installations on aircraft registered in countries under EASA oversight.
2. Complete the Post Installation Checkout Procedure in Section 7.6 of the 600-00299-000, IFD5XX/IFD4XX Installation Manual.
3. For installation on aircraft registered in countries under EASA oversight:
a. Application of this STC in countries under EASA oversight no longer requires the installation to be approved as a minor change. Installers must make sure the installation is fully within the bounds of the IFD5XX/IFD4XX Installation Manual 600-00299-000. For example, if the IFD is interfaced to equipment listed in Section 2.3 of the IFD5XX/IFD4XX Installation Manual, then those interfaces are within the bounds of the IFD5XX/IFD4XX Installation Manual. Only the interfaces to equipment models explicitly listed in Section 2.3 are approved by this STC (with the exception of COM and NAV radios as dictated by the NOTE below). Autopilot coupling is not permitted under this STC unless that autopilot is explicitly listed in Section 2.3 of the IFD5XX/IFD4XX Installation Manual.
NOTE: COM and NAV radios that are not listed in Section 2.3 but meet all of the criteria in that section are approved by this STC.
b. As part of the aircraft modification, fill out the data in Sections 5 through 7 of this document (AVIFD-484).
The purpose of this data is to document the manner in which the STC was applied to your particular aircraft.
c. Keep a copy of the following completed forms with the aircraft permanent records:
i. Section 5 through 7 forms
ii. Appendix F of 600-00299-000, IFD5XX/IFD4XX Installation Manual
iii. Post Installation Checkout Procedure in Section 7.6 of the 600-00299-000, IFD5XX/IFD4XX Installation Manual
4. If the installation is beyond the bounds of the IFD5XX/IFD4XX Installation Manual, then further airworthiness approval may be required.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
4. Additional Requirements
The following requirements are in addition to those specified in the IFD5XX/IFD4XX Installation Manual for installations on aircraft registered in countries under EASA oversight.
· The EASA Approved Flight Manual Supplement for this alteration must be attached to the airplanes existing AFM/POH; EASA Approved Airplane Flight Manual Supplement For (make and model) with Avidyne Integrated Flight Displays p/n 70000182-XXX and 700-00179-XXX, document number 600-00298-001, Rev 00 or later approved revision.
· The V-Flag State setting in maintenance mode under Main CDI / OBS Config page must be set to Normal.
· Com Frequency Spacing setting under AUX page/Setup tab/User Options must be set to 8.33 KHz.
· Pressure Units setting under AUX page/Setup tab/User Options must be set to mbar.
· Temperature Units setting under AUX page/Setup tab/User Options must be set to Celsius.
· Fuel Units setting under AUX page/Setup tab/User Options may be set to Gallons, Imp. Gallons or Liters.
· The pilot-selectable field `DIS' (Distance to Current Waypoint) datablock must be configured in the location on the Map page (IFD4XX and IFD5XX) and Default Nav page (IFD4XX only) that is closest to the pilot's primary field of view. Reference the `Map Data Fields' section of the IFD440 Pilot's Guide (600-00304-000), IFD410 Pilot's Guide (600-00319-000) and IFD540 Pilot's Guide (600-00300-001), IFD510 Pilot's Guide (600-00318-000) or IFD545 / IFD550 Pilot's Guide (600-00317-000).
· No aircraft, performance or procedure checklists may be loaded into the IFD4XX/IFD5XX.
· The IFD4XX/IFD5XX are not approved TAWS-B sensor/displays. Terrain alerting functions of the IFD4XX/IFD5XX are non-TSO functions that are advisory only.
· WiFi and Bluetooth wireless features may not be used during critical phases of flight to include takeoff, approaches, landing. WiFi and Bluetooth must be selected off on the user setup tab (SYS/Setup) during these phases of flight.
· ADS-B out capability is not approved for State aircraft operating IFR/GAT in Europe for the Avidyne IFD4XX/IFD5XX navigator installed in conjunction with Garmin GTX330ES or Garmin GTX335/GTX345.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
5. Weight and Balance
Complete a weight and balance calculation according to Section 5.9 of the IFD 5XX/4XX Installation Manual and record the calculations in Table 5-1.
Description of items added to aircraft
Weight
Arm
Moment
Subtotal:
Description of Items Removed from Aircraft
Weight
Arm
Moment
Subtotal:
Total Change:
Previous aircraft weight and balance Change in aircraft weight and balance New aircraft weight and balance Are results within operating limits of aircraft? (circle one) Comments:
YES
NO
Table 5-1. Weight and Balance
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
6. Electrical Load Analysis
An electrical load analysis (ELA) must be completed on each aircraft prior to installation to verify that the aircraft electrical system is capable of supporting the equipment installed using this STC. The purpose of the ELA is to show compliance with EASA CS 23.1351 and 23.1353(h). If it is determined that the modification results in an increase in electrical load then it must be further verified that the aircraft electrical system remains in compliance which includes verification of electrical generation capacity and verification that reserve battery capacity remains adequate to support loads essential to continued safe flight and landing.
There are several approaches that may be taken, as described in the following sections. For each approach, use the instructions in Section 4.10 of the IFD5XX/4XX Installation Manual.
6.1 Aircraft with Existing Electrical Load Analysis
If there is an existing ELA for the aircraft, it must be updated to reflect the modification. It must show that the alternators/generators have adequate capacity to supply power to the modified systems in all anticipated conditions. Add the applicable typical current draw values from Section 1-4 of the IFD 5XX/4XX Installation Manual to the existing ELA under continuous operating conditions. Ensure that the new aircraft electrical load does not exceed the rated capacity of the installed generator/alternator.
If the new aircraft electrical load does not exceed the rated capacity of the installed generator/alternator, include the updated ELA along with this document (AVIFD-484).
After performing the calculations, if the additional load of the IFD4XX and/or IFD5XX exceeds the rated capacity of the generator/alternator, proceed to Section 6.4. If the additional electrical load still exceeds the generator rated capacity, alternate regulatory approval is required for installation of the equipment in the aircraft.
6.2 Aircraft without Existing Electrical Load Analysis
Prior to undertaking a complete electrical load analysis, the net change to the electrical load resulting from the IFD4XX and/or IFD5XX installation should be determined. The results of this analysis will determine how to proceed further.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
Description of Items Added to Aircraft
Electrical Load (A)
Subtotal:
Description of Items Removed from Aircraft
Electrical Load (A)
Subtotal:
Net Change in Bus Load: Table 6-1. Electrical Load Analysis (Calculated)
6.3 Electrical Load is Reduced Following Modification
In many instances when older systems are replaced with newer equipment, the electrical load presented to the power system may be reduced. If the overall load on the electrical system is reduced as a result of the equipment installation, no further analysis is required. This assumes that the electrical system was within all limits prior to the IFD4XX and/or IFD5XX installation.
This amended electrical load calculation (Table 6-1) must be included with this document (AVIFD-484) to document the electrical load reduction.
6.4 Electrical Load is Increased Following Modification
If it is determined that the electrical load has increased, a complete electrical load analysis must be performed to show that the capacity of the alternator/generator and battery are sufficient for the additional electrical load. For guidance on preparing an ELA, refer to ASTM F 2490-05: Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis.
This complete electrical load analysis must be included with this document (AVIFD-484) to document the electrical load analysis results.
Alternatively, the loads under various operating conditions may be measured, as described in Section 6.5.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
6.5 Performing an Electrical Load Analysis by Measurement
NOTE: According to EASA CS 23.1351(a) (2) (ii), performing an ELA using electrical measurements is not acceptable for commuter category airplanes.
If measurements are used for the electrical load, follow the instructions in Section 9 of ASTM F 2490-05: Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis to complete Table 6-2. If the Blank Emergency Power Calculation Form is utilized, include a completed copy of the form with this document.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
Date:
Electrical Load Measurement
Registration No:
Circuit/ System
Circuit Load Breaker No.
Operating Time
Normal Operation Taxing TO/Land 10 min 10 min
Used in this phase of flight?
Used in this phase of flight?
Cruise 60 min
Used in this phase of flight?
Table 6-2. Electrical Load Analysis (Measured)
Emergency Operation
Cruise
Land
(calculated) 10 min
Used in
Used in
this phase this phase
of flight? of flight?
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
Circuit/ System
Circuit Breaker No.
Electrical Load Measurement (cont'd)
Taxing 10 min
Normal
Operation
TO/Land Cruise
10 min
60 min
Load
Operating Time
Used in this phase of flight?
Used in this phase of flight?
Used in this phase of flight?
Emergency Operation
Cruise
Land
(calculated) 10 min
Used in
Used in
this phase this phase
of flight?
of flight?
MEASURED VALUE
(Amps) _______
Alternator Rating (Amps):
Ldg light ON
(b1)
(a)
Ldg light
(c)
OFF
(b2)
(d)
(e)
Percent of Alternator Capacity Used:
(< 80 %)
Ldg light ON (< 95%)
(< 80 %
Ldg light OFF (< 80%)
N/A
N/A
It is permissible to exceed 80% of the alternator data plate rating during the takeoff/landing phase of flight when the pitot heat and landing light are switched on simultaneously. However, for this condition (i) you must not exceed 95% of the alternator data plate rating, and (ii) you must not exceed 80% of the alternator data plate rating with the pitot heat on and the landing light off.
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EASA Installation Checklist
IFD4XX and IFD5XX Series AML STC
7. Post Installation Verification
The following items are to be verified after the installation has been completed.
· Circuit breaker(s) installed as part of this STC are labeled as specified in Section 4.8 of the IFD 5XX/IFD4XX Installation Manual.
· Circuit breaker(s) installed as part of this STC are readily accessible to the pilot.
· Wiring is routed in a safe manner as described in Section 4.3 of the IFD 5XX/IFD4XX Installation Manual.
· Structural aspects of the installation follow the instructions in Section 5 and Appendix C in the IFD 5XX/IFD4XX Installation Manual, or from separate installation approval that has been or will be obtained.
· IFD's do not cause objectionable interference with other equipment in the aircraft. Verify by completing the EMI/RFI Checks in Section 7.6.7 of the IFD 5XX/IFD4XX Installation Manual.
7.1 Database updates
Periodic updates to navigation data, charts data, and obstacle data are all made through the USB port on the front of each IFD. Database updates (SW) require EASA Form 1 or equivalent approved means such as Jepp online data retrieval method(s).
The table below summarizes the databases update periods:
Database
Update Cycle
Comments & Source
Chart Data 14 days
Expiration watermark displayed after 14 days indefinitely until data updated (Jeppesen)
Nav Data 28 days
Airport, airway, navaid, airspace, and FMS data (Jeppesen)
Obstacle Data
56 days
Displayed on map and used for TA and FLTA functions (Jeppesen)
Terrain Data
As required
Displayed on map and used for TA and FLTA functions. The IFD is shipped from the factory with this database already loaded and updates are anticipated to be a rare occurrence.
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