AIR TRANSPORT AVIONICS EQUIPMENT
INTERFACES
ARINC SPECIFICATION 600-20
PUBLISHED: July 11, 2017
Prepared by the AEEC
Published by
SAE ITC
16701 Melford Blvd., Suite 120, Bowie, Maryland 20715 USA
DISCLAIMER
THIS DOCUMENT IS BASED ON MATERIAL SUBMITTED BY VARIOUS PARTICIPANTS
DURING THE DRAFTING PROCESS. NEITHER AEEC, AMC, FSEMC NOR SAE ITC HAS
MADE ANY DETERMINATION WHETHER THESE MATERIALS COULD BE SUBJECT TO
VALID CLAIMS OF PATENT, COPYRIGHT OR OTHER PROPRIETARY RIGHTS BY THIRD
PARTIES, AND NO REPRESENTATION OR WARRANTY, EXPRESS OR IMPLIED, IS
MADE IN THIS REGARD.
ARINC INDUSTRY ACTIVITIES USES REASONABLE EFFORTS TO DEVELOP AND
MAINTAIN THESE DOCUMENTS. HOWEVER, NO CERTIFICATION OR WARRANTY IS
MADE AS TO THE TECHNICAL ACCURACY OR SUFFICIENCY OF THE DOCUMENTS,
THE ADEQUACY, MERCHANTABILITY, FITNESS FOR INTENDED PURPOSE OR
SAFETY OF ANY PRODUCTS, COMPONENTS, OR SYSTEMS DESIGNED, TESTED,
RATED, INSTALLED OR OPERATED IN ACCORDANCE WITH ANY ASPECT OF THIS
DOCUMENT OR THE ABSENCE OF RISK OR HAZARD ASSOCIATED WITH SUCH
PRODUCTS, COMPONENTS, OR SYSTEMS. THE USER OF THIS DOCUMENT
ACKNOWLEDGES THAT IT SHALL BE SOLELY RESPONSIBLE FOR ANY LOSS, CLAIM
OR DAMAGE THAT IT MAY INCUR IN CONNECTION WITH ITS USE OF OR RELIANCE
ON THIS DOCUMENT, AND SHALL HOLD AEEC, AMC, FSEMC, SAE ITC, AND ANY
PARTY THAT PARTICIPATED IN THE DRAFTING OF THE DOCUMENT HARMLESS
AGAINST ANY CLAIM ARISING FROM ITS USE OF THE STANDARD.
THE USE IN THIS DOCUMENT OF ANY TERM, SUCH AS SHALL OR MUST, IS NOT
INTENDED TO AFFECT THE STATUS OF THIS DOCUMENT AS A VOLUNTARY
STANDARD OR IN ANY WAY TO MODIFY THE ABOVE DISCLAIMER. NOTHING HEREIN
SHALL BE DEEMED TO REQUIRE ANY PROVIDER OF EQUIPMENT TO INCORPORATE
ANY ELEMENT OF THIS STANDARD IN ITS PRODUCT. HOWEVER, VENDORS WHICH
REPRESENT THAT THEIR PRODUCTS ARE COMPLIANT WITH THIS STANDARD SHALL
BE DEEMED ALSO TO HAVE REPRESENTED THAT THEIR PRODUCTS CONTAIN OR
CONFORM TO THE FEATURES THAT ARE DESCRIBED AS MUST OR SHALL IN THE
STANDARD.
ANY USE OF OR RELIANCE ON THIS DOCUMENT SHALL CONSTITUTE AN
ACCEPTANCE THEREOF “AS IS” AND BE SUBJECT TO THIS DISCLAIMER.
This document is published information as defined by 15 CFR Section 734.7 of the Export Administration Regulations (EAR). As publicly available technology under 15 CFR 74.3(b)(3), it is not
subject to the EAR and does not have an ECCN. It may be exported without an export license.
©2017 BY
SAE INDUSTRY TECHNOLOGIES CONSORTIA (SAE ITC)
16701 MELFORD BLVD., SUITE 120, BOWIE, MARYLAND 20715 USA
ARINC SPECIFICATION 600-20
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: July 11, 2017
Specification 600
Specification 600-1
Specification 600-2
Specification 600-3
Specification 600-4
Specification 600-5
Specification 600-6
Specification 600-7
Specification 600-8
Specification 600-9
Specification 600-10
Specification 600-11
Specification 600-12
Specification 600-13
Specification 600-14
Specification 600-15
Specification 600-16
Specification 600-17
Specification 600-18
Specification 600-19
Specification 600-20
Prepared by the Airlines Electronic Engineering Committee (AEEC)
Adopted by the AEEC Executive Committee
Adoption Date
July 21, 1977
Supplements to this ARINC Standard
May 4, 1978
August 30, 1979
March 11, 1981
December 10, 1981
November 2, 1982
October 13, 1983
October 8, 1986
November 8, 1990
November 4, 1992
November 2, 1995
October 16, 1997
April 29, 1998
March 15, 2001
October 15, 2003
October 4, 2005
October 11, 2006
October 28, 2009
March 31, 2010
April 20, 2011
May 3, 2017
Published Date
December 17, 1977
August 1, 1978
November 15, 1979
April 15, 1981
February 8, 1982
August 12, 1983
November 28, 1983
December 26, 1986
January 23, 1991
June 10, 1993
November 20, 1995
November 10, 1998
November 10, 1998
March 30, 2001
July 1, 2004
January 1, 2006
November 22, 2006
February 16, 2010
May 10, 2010
June 23, 2011
July 11, 2017
A summary of the changes introduced by each supplement is included at the end of this document.
FOREWORD
The AEEC, SAE ITC, and ARINC Standards
ARINC Industry Activities, an SAE ITC program, organizes aviation industry committees
and participates in related industry activities that benefit aviation at large by providing
technical leadership and guidance. These activities directly support aviation industry
goals: promote safety, efficiency, regularity, and cost-effectiveness in aircraft operations.
ARINC Industry Activities organizes and provides the secretariat for international aviation
organizations (AEEC, AMC, FSEMC) which coordinate the work of aviation industry
technical professionals and lead the development of technical standards for airborne
electronic equipment, aircraft maintenance equipment and practices, and flight simulator
equipment used in commercial, military, and business aviation. The AEEC, AMC, and
FSEMC develop consensus-based, voluntary standards that are published by SAE ITC
and are known as ARINC Standards. The use of ARINC Standards results in substantial
technical and economic benefit to the aviation industry.
There are three classes of ARINC Standards:
a)
ARINC Characteristics – Define the form, fit, function, and interfaces of avionics
and other airline electronic equipment. ARINC Characteristics indicate to
prospective manufacturers of airline electronic equipment the considered and
coordinated opinion of the airline technical community concerning the requisites of
new equipment including standardized physical and electrical characteristics to
foster interchangeability and competition.
b)
ARINC Specifications – Are principally used to define either the physical
packaging or mounting of avionics equipment, data communication standards, or
a high-level computer language.
c)
ARINC Reports – Provide guidelines or general information found by the airlines
to be good practices, often related to avionics maintenance and support.
The release of an ARINC Standard does not obligate any organization to purchase
equipment so described, nor does it establish or indicate recognition or the existence of
an operational requirement for such equipment, nor does it constitute endorsement of any
manufacturer’s product designed or built to meet the ARINC Standard.
In order to facilitate the continuous product improvement of this ARINC Standard, two
items are included in the back of this document:
An Errata Report solicits any corrections to existing text or diagrams that may be
included in a future Supplement to this ARINC Standard.
An ARINC IA Project Initiation/Modification (APIM) form solicits any proposals for
the addition of technical material to this ARINC Standard.
ii
ARINC SPECIFICATION 600
TABLE OF CONTENTS
1.0
1.1
1.2
1.3
1.4
1.4.1
1.4.2
1.4.3
1.4.4
1.4.4.1
1.4.5
1.4.6
1.4.7
1.4.8
1.4.9
GENERAL CONSIDERATIONS..................................................................................... 1
Objectives ...................................................................................................................... 1
Scope ............................................................................................................................. 2
Principles ....................................................................................................................... 3
Nomenclature and Definitions ........................................................................................ 4
The Modular Concept Unit (MCU) ............................................................................. 4
The Equipment Rack and Shelf................................................................................. 4
LRU Guides ............................................................................................................... 4
The Electrical Interface.............................................................................................. 5
Electrical Power Supply ........................................................................................ 5
Wire Integration ......................................................................................................... 5
Cooling Air Ducts and Plenums................................................................................. 5
Standard International (S.I.) Units ............................................................................. 6
Other Environmental Considerations ........................................................................ 6
Related Documents ................................................................................................... 6
2.0
2.1
2.2
INTERCHANGEABILITY ............................................................................................... 7
LRU Interchangeability ................................................................................................... 7
Cabinets, Racks, and Shelves Interchangeability .......................................................... 7
3.0
PHASE 1 DESIGN REQUIREMENTS ........................................................................... 8
3.1
The MCU ........................................................................................................................ 8
3.1.1
Form Factor and Case Dimensions ........................................................................... 8
3.1.1.1
LRU Hold-Downs .................................................................................................. 8
3.1.1.2
Front Panel Protrusions ........................................................................................ 9
3.1.1.3
Rear Panel ............................................................................................................ 9
3.1.1.4
Maximum Weight .................................................................................................. 9
3.1.1.5
Indexing ................................................................................................................ 9
3.1.1.6
Mating Force ....................................................................................................... 10
3.1.1.7
MCU Backplate Deflection .................................................................................. 10
3.1.2
Vibration, Shock, and Acceleration ......................................................................... 10
3.1.3
Cooling .................................................................................................................... 10
3.1.3.1
Cooling Air Interface ........................................................................................... 11
3.1.3.2
Power Dissipation ............................................................................................... 11
3.1.4
LRU Evaluation ....................................................................................................... 11
3.2
The Equipment Rack/Cabinet ...................................................................................... 11
3.2.1
Datum and Method of Dimensioning ....................................................................... 12
3.2.2
MCU Spacing on Rack Shelf ................................................................................... 12
3.2.3
Mechanical Interface with the LRU.......................................................................... 12
3.2.3.1
Backplate Assembly ........................................................................................... 13
3.2.3.1.1
Gauging of the Shelf Backplate ..................................................................... 13
3.2.3.1.2
Rack Backplate Deflection ............................................................................. 13
3.2.3.2
Front Retainer ..................................................................................................... 13
3.2.3.2.1
LRU Hold-Down Details ................................................................................. 13
3.2.3.2.2
LRU Extractor Details .................................................................................... 14
3.2.3.3
Mass of LRU Load .............................................................................................. 14
3.2.4
Electrical Bonding Interface..................................................................................... 14
3.2.5
Environmental Interface Considerations ................................................................. 14
3.2.5.1
Vibration, Shock, and Accelerations ................................................................... 15
3.2.5.2
Thermal Interface ............................................................................................... 15
3.2.6
Equipment Rack Appraisal ...................................................................................... 16
3.2.7
Rack Maintenance and Accessibility ....................................................................... 16
iii
ARINC SPECIFICATION 600
TABLE OF CONTENTS
3.3
The Rack and Panel Connector ................................................................................... 16
3.3.1
Connector Electrical Considerations ....................................................................... 18
3.3.1.1
Contacts ............................................................................................................. 18
3.3.1.2
Deleted by Supplement 2 ................................................................................... 18
3.3.1.3
Electrical Circuits ................................................................................................ 18
3.3.1.4
Family of Connectors .......................................................................................... 18
3.3.1.5
Shell .................................................................................................................... 18
3.3.1.6
Inserts ................................................................................................................. 18
3.3.1.7
Intermateability ................................................................................................... 18
3.3.1.8
Conntector-to-Wire Interface .............................................................................. 19
3.3.2
Connector Mechanical Considerations.................................................................... 19
3.3.2.1
Shell Strength ..................................................................................................... 19
3.3.2.2
Shell .................................................................................................................... 19
3.3.2.3
Envelope and Configuration ............................................................................... 19
3.3.2.4
Engage and Disengage Forces .......................................................................... 20
3.3.2.4.1
Future Designs............................................................................................... 20
3.3.2.4.2
Existing Designs ............................................................................................ 20
3.3.2.5
Moving Mechanism ............................................................................................. 20
3.3.2.6
Contact Actuator ................................................................................................. 20
3.3.2.7
Failure Mode ....................................................................................................... 20
3.3.2.8
Signal Contact .................................................................................................... 21
3.3.2.9
Indexing Capability ............................................................................................. 21
3.3.2.10
Index Numbering ................................................................................................ 21
3.3.2.11
Partial Contacts .................................................................................................. 21
3.3.2.12
Fiber Optic Termini ............................................................................................. 21
3.3.2.12.1
Cable Selection .............................................................................................. 22
3.3.2.12.2
ARINC 600 Connector Termini Layout .......................................................... 23
3.3.3
Connector Environmental Considerations ............................................................... 23
3.3.4
Connector Tooling and Maintenance Consideration ............................................... 23
3.3.4.1
Flight Line Tooling .............................................................................................. 23
3.3.4.2
Termination ......................................................................................................... 24
3.3.4.3
Manufacture Identification .................................................................................. 24
3.3.5
Connector Installation Considerations..................................................................... 24
3.3.5.1
The LRU Electrical Interface ............................................................................... 24
3.3.5.1.1
Connector Position......................................................................................... 25
3.3.5.2
The Rack/Cabinet Electrical Interface ................................................................ 25
3.3.5.2.1
Backplate Connector Positions ...................................................................... 27
3.3.5.2.2
Backplate Deflection ...................................................................................... 27
3.4
Wire Integration ............................................................................................................ 27
3.4.1
Mechanical Interface Consideration ........................................................................ 27
3.4.1.1
Location of Integration Center ............................................................................ 27
3.4.1.2
Electrical Termination ......................................................................................... 27
3.4.1.3
Ease of Maintenance .......................................................................................... 27
3.4.1.4
Indexing .............................................................................................................. 28
3.4.2
Electrical Interface Considerations .......................................................................... 28
3.4.2.1
Non-Customization ............................................................................................. 28
3.4.2.2
Identification and Accessibility ............................................................................ 28
3.4.2.3
Circuits Accommodation ..................................................................................... 28
3.4.2.4
Physical Barriers ................................................................................................. 28
3.4.2.5
Grounding ........................................................................................................... 28
3.4.3
Environmental Considerations ................................................................................ 28
3.4.4
Tooling and Maintenance Consideration ................................................................. 28
iv
ARINC SPECIFICATION 600
TABLE OF CONTENTS
3.5
3.5.1
3.5.1.1
3.5.1.2
3.5.1.3
3.5.1.4
3.5.1.5
3.5.1.6
3.5.2
3.5.3
3.5.4
3.5.4.1
3.5.4.2
3.5.4.3
3.5.4.4
3.5.4.5
3.5.4.6
3.5.4.7
3.5.5
3.5.6
3.5.6.1
3.5.6.2
3.5.7
3.6
3.6.1
3.6.2
3.7
Thermal Management .................................................................................................. 28
Definitions................................................................................................................ 28
Electronic Part .................................................................................................... 28
Temperature Critical Parts .................................................................................. 28
Stabilization ........................................................................................................ 29
Maximum Steady State Heat Dissipation ........................................................... 29
Ambient Temperature ......................................................................................... 29
Thermal Design Condition .................................................................................. 29
Electronic Part Application ...................................................................................... 29
Ambient Temperature.............................................................................................. 30
Coolant Air............................................................................................................... 31
Coolant Air, Bulk Temperature at the LRU Inlet, Minimum to Maximum ............ 31
Coolant Air Relative Humidity ............................................................................. 31
Coolant Air Flow Rate ......................................................................................... 31
Coolant Air Quality .............................................................................................. 32
Coolant Air Pressure Drop through the Equipment Level 1 and Level 2 ............ 32
Coolant Air Inlet and Outlet Locations ................................................................ 32
Coolant Air Leakage from the Equipment ........................................................... 33
Equipment Sidewall Temperature ........................................................................... 33
LRU Thermal Appraisal ........................................................................................... 33
Identification and Data Tabulation for Heat Dissipating and Temperature
Critical Parts ........................................................................................................ 33
Thermal Evaluation Test ..................................................................................... 34
Thermal Interface Information ................................................................................. 34
Power Quality and Power Conditioning ....................................................................... 35
Power Quality .......................................................................................................... 35
Power Conditioning ................................................................................................. 35
Mechanical and Structural Appraisals .......................................................................... 35
ATTACHMENTS
ATTACHMENT 1
ATTACHMENT 2
ATTACHMENT 3
ATTACHMENT 4
ATTACHMENT 5
ATTACHMENT 6
ATTACHMENT 7
ATTACHMENT 8
ATTACHMENT 9
ATTACHMENT 10
ATTACHMENT 11
ATTACHMENT 12
ATTACHMENT 13
ATTACHMENT 14
ATTACHMENT 15
ATTACHMENT 16
ATTACHMENT 17
ATTACHMENT 18
TYPICAL RACK ASSEMBLY ....................................................................... 36
STANDARD LRU CASE SIZE ..................................................................... 37
LOCATION OF CONNECTOR ..................................................................... 40
MAXIMUM LRU WEIGHT ............................................................................ 41
SHELF/RACK DATUMS .............................................................................. 42
STANDARD SHELF DATUM LINE GRID AND LRU LOCATIONS.............. 43
LRU HOLD DOWN MECHANISMS ............................................................. 44
SHELF/RACK DIMENSIONS FOR LRU GUIDES ....................................... 46
COOLING APERTURES .............................................................................. 48
DELETED................................................................................................... 51
CONTACT POSITION IDENTIFICATION AND INSERT SIZE .................. 52
MAXIMUM LRU THERMAL DISSIPATION ................................................ 65
ENVIRONMENTAL CONDITIONS FOR ELECTRICAL/ELECTRONIC
EQUIPMENT INSTALLED IN CONTROLLED TEMPERATURE AND
PRESSURIZED LOCATIONS .................................................................... 66
THERMAL APPRAISAL TEST ................................................................... 67
LRU MOUNTING PATTERN – SIZE 1 CONNECTOR............................... 82
SHELF/RACK CUTOUT – SIZE 1 CONNECTOR...................................... 86
CONNECTOR ENGAGING SEQUENCE .................................................. 89
INDEX PIN CODING .................................................................................. 90
v
ARINC SPECIFICATION 600
TABLE OF CONTENTS
ATTACHMENT 19
ATTACHMENT 20
ATTACHMENT 21
CONNECTOR SPECIFICATION ............................................................... 96
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS
SIZE 8 QUADRAX TYPE ......................................................................... 218
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS
SIZE 8 TWINAX TYPE ............................................................................. 247
APPENDICES
APPENDIX 1
APPENDIX 2
APPENDIX 3
APPENDIX 4
APPENDIX 5
NOT USED ....................................................................................................... 250
ENVIRONMENTAL REQUIREMENTS FOR MILITARY APPLICATIONS ....... 251
TYPICAL ASSEMBLY INSTRUCTIONS, SIZE 1 RF CONTACT ..................... 253
GUIDELINES FOR AVIONICS 10/100BASE-T ETHERNET CONNECTOR
CHARACTERISTICS SIZE 8 QUADRAX TYPE .............................................. 256
ETHERNET CONTACT CONSIDERATIONS FOR NEW DESIGNS ............... 259
vi
ARINC SPECIFICATION 600 – Page 1
1.0 GENERAL CONSIDERATIONS
1.0 GENERAL CONSIDERATIONS
1.1 Objectives
ARINC 600 is intended to take advantage of technical and procedural
advancements that were not available to those who developed ARINC Specification
404A, providing mechanical, electrical, and environmental interface information for
air transport avionics design and installation. Earlier industry avionics packaging
developments evolved into the Air Transport Radio (ATR) boxes which have been
covered by the previous ARINC Specification 404 since 1956. Industry experience
has demonstrated the need for new installation concepts to avoid problems resulting
from the growing complexity of avionics equipment. The concepts which address
these needs form the basis of this standard.
ARINC 600 was prepared at a time when equipment and installations were
designed to meet ARINC 404A, and they existed in large numbers.
COMMENTARY
ARINC 404A is not superseded by this document but rather,
supplemented by it. There will continue to be avionic boxes best
served by ARINC 404A even to this day. Airlines desire that the use
of technical advancements should be enabled by an evolutionary
process rather than through revolutionary and drastic changes taking
place in such a way that great financial, technical, and logistic impact
is an inherent risk. In view of this, ARINC 600 has set forth an
evolutionary method of implementing proved and desired technical
and procedural advancements in making and providing for avionics
boxes. A further principle the airlines intended to make clear is that
the electronic equipment installed in air transport aircraft are
fundamental to the use of these aircraft. Since the aircraft use is
totally dependent on the adequate functioning of this electronic
equipment, the aircraft will take an equal, co-partner role with the
avionics equipment in assuring that conditions are met for reliable
and still cost effective electronics performance. It is intended that the
avionics equipment standards can be written so as to reduce costs
associated with control of power, meeting environmental
requirements, providing multiple kilo-hour mean time between failure
guarantees, and enhancing means of removing only failed boxes to
reduce the incidence of unconfirmed removals.
ARINC 600 sets forth:
a. The definition, guidance, and appraisal for design and acceptance of the
mechanical, electrical and environmental interfaces between Line
Replaceable Units (LRUs) and the racks or cabinets in which they are
installed.
b. The definition, guidance, and appraisal for design and acceptance of the
mechanical, electrical, and environmental interfaces between racks or
cabinets and the aircraft in which they are installed.
c. The definition, guidance, and appraisal for the control and regulation of
aircraft power as applied to air transport avionics.
ARINC SPECIFICATION 600 – Page 2
1.0 GENERAL CONSIDERATIONS
d. The definition, guidance, and appraisal of the provision for Airborne
Automatic Test Equipment (ABATE) but not the testing and test criteria
themselves.
COMMENTARY
The NIC Subcommittee originally envisioned a system of avionics in
which each LRU could be automatically tested by test equipment
permanently installed in the racks to perform that function. If an LRU
were to malfunction, it was intended that this would be indicated to
line maintenance personnel by lights or some equivalent means.
Knowing which LRU to remove would greatly reduce the unconfirmed
removal rate. The NIC Subcommittee ultimately concluded that test
criteria and test equipment descriptions were beyond the scope of
ARINC 600. However, the principles are so highly regarded that the
provisions for ABATE are included in this document as a reminder to
those concerned with the development of avionics standards.
1.2 Scope
It is intended that ARINC 600 be used with the application and customer needs in
mind. To enhance the breadth of use, this document alludes to three phases defined
as follows:
a. Phase I – This phase specifies the definitions, guidance, and appraisals
given in Section 1.1 for those instances in which the aircraft manufacturer
intends to randomly mix ARINC 600 boxes and ARINC 404A boxes.
COMMENTARY
In some aircraft, ARINC 600 boxes will be interspersed with ARINC
404A boxes in one rack while others will be installed in a dedicated
ARINC 600 rack/cabinet. The guiding principle in this Specification is
one-way generation interchangeability. ARINC 600 Phase I boxes
should meet qualification requirements and fit and perform
satisfactorily when installed on a Phase 0 (ARINC 404A) rack. It is
recognized that a portion of the ARINC 404A rack will have to be
made to accommodate the ARINC 600 Phase I boxes due to different
hold-downs and different connectors. This is not to imply that cooling
air will be different. Air will continue to be drawn down in ARINC 404A
racks and ARINC 600 Phase I boxes will have to live with this
condition. On the other hand, an ARINC 404A box could not be
installed in an ARINC 600 Phase I rack/cabinet because it may be
too large, it has front “dog houses,” a cooling system (e.g., holes in
the sides of the LRU) that would upset the cooling provided in an
ARINC 600 Phase I rack/cabinet, and for other reasons. The user of
this Specification may, therefore, always install a mix of boxes in the
lower numbered phase rack/cabinet and only two phases will be
mixed in one rack/cabinet.
b. Phase II – This phase was envisioned to specify the definitions, guidance,
and appraisals for those instances where ARINC 600 boxes are of a design
catering to mechanical, electrical, and environmental control that is
substantially beyond those features for Phase I. Phase II, therefore, is
another step in the evolutionary development of avionic installations. As with
ARINC SPECIFICATION 600 – Page 3
1.0 GENERAL CONSIDERATIONS
Phase I and ARINC 404A, it is likely that aircraft manufacturers will find it
necessary or convenient to sometimes mix Phase II and Phase I boxes in a
rack. When this is done, the installation criteria for Phase I will prevail.
However, it would not be proper to install Phase II boxes in ARINC 404A
shelves. The standard rule is to always install a mix of boxes in the lowernumbered phase shelf/cabinet and no more than two phases may be mixed
on one shelf. Put differently, a Phase N+1 box can be used in (and only in) a
Phase N or a Phase N+1 rack/cabinet. Similarly, a Phase N box can be used
only in a Phase N or Phase N-1 rack/cabinet.
COMMENTARY
The Commentary set forth in (a.) above applies. It must be clearly
understood that Phase II has not been defined.
c. Phase III – This phase was envisioned to specify the definitions, guidance,
and appraisals for those instances where ARINC 600 boxes are of a design
catering to improved mechanical, electrical, and environmental control that is
substantially beyond those features for Phase II. The criteria for mixing
Phase II and Phase III boxes include the requirement that such a mix must
always occur in a Phase III rack/cabinet only.
COMMENTARY
The commentary under (a.) and (b.) applies. It must be clearly
understood that Phase III has not been defined.
NIC Phase I Design Requirements are contained in Section 3 of this
document.
1.3 Principles
Application of ARINC 600 will provide:
a. A system of modularized equipment.
b. A system of modularized installation in racks and/or cabinets.
c. A family of low or zero insertion force electrical connectors to provide the
electrical interface between the equipment and the aircraft wiring.
d. A system of effective environmental control of the equipment.
e. Methods of appraisal to provide data which may be used by the equipment
and aircraft manufacturers to ensure compatibility of the equipment and the
aircraft environment in the attainment of basic air transport requirements.
Inherent in this point is the principle that failure of an LRU resulting from the
mechanical, electrical, and environmental interfaces encountered on the
aircraft can be avoided, and that aircraft providing the interfaces as stated
herein, cannot be held responsible for failures of this nature.
COMMENTARY
This document is provided for use by the commercial air transport
industry, including airline operators, airframe manufacturers, and
avionics equipment manufacturers. The AEEC Subcommittees
developing standards for avionic systems are expected to adhere to
these requirements when creating Characteristics for new systems. It
is strongly desired that this Specification will also be used by the
ARINC SPECIFICATION 600 – Page 4
1.0 GENERAL CONSIDERATIONS
military and general aviation organizations for avionics equipment
installations.
1.4 Nomenclature and Definitions
Attachment 1 shows an expanded view of the New Installation Concept. Each of the
hardware items identified is discussed below.
1.4.1
The Modular Concept Unit (MCU)
The basic unit around which the entire packaging and installation concept is based
is designated the Modular Concept Unit (MCU). The MCU has a fixed height, length,
and width. A unit having a minimum allowable width is designated as a 1 MCU and
all other sizes are expressed in terms of multiples of 1 MCU, e.g., 2 MCU, etc.
The correlations between ARINC 600 MCU sizes and ARINC 404A ATR short box
sizes are based on the following approximate equivalencies:
Table 1-1
Box Size Comparison1
ARINC 600
ARINC 404A
12 MCU
1 1/2 ATR
11 MCU
1 3/8 ATR2
10 MCU
1 1/4 ATR2
9 MCU
1 1/8 ATR2
8 MCU
1 ATR
7 MCU
7/8 ATR2
6 MCU
3/4 ATR
5 MCU
5/8 ATR2
4 MCU
1/2 ATR
3 MCU
3/8 ATR
2 MCU
1/4 ATR
1 MCU
1/8 ATR2
Notes:
1. MCU length is approximately equivalent to an ATR short.
2. ATR equivalents that do not exist in ARINC 404A.
1.4.2
The Equipment Rack and Shelf
The designation “equipment rack” pertains to the structure on which a number of
LRUs are installed. The equipment rack should be designed so best use can be
made of the available floor-to-ceiling space often resulting in more than one tier of
equipment. The structure upon which any one tier of equipment is mounted is
designated a shelf. Shelves provide the support points which mechanically fit the
LRU to the rack, electrically interface the LRU with the aircraft wiring and other
LRUs, and interface the LRU with the equipment cooling system. An equipment rack
may be open, partially enclosed, or may be entirely enclosed to meet specific
requirements. An entirely enclosed rack with access doors is called a cabinet.
1.4.3
LRU Guides
LRU guides (e.g., rails or trays) on the shelf provide dimensional control between
the LRU, the rack connector, and the cooling air interface.
ARINC SPECIFICATION 600 – Page 5
1.0 GENERAL CONSIDERATIONS
1.4.4
The Electrical Interface
The electrical interface between the LRU and the aircraft wiring is provided by a low
insertion force or zero insertion force rack and panel connector. The metal or
structural component on which the rack half of the connector is mounted to the rack
is designated as the backplate.
COMMENTARY
The words “Low Insertion Force” and “Zero Insertion Force” are used
throughout this document to describe the connector. The limits of
these forces are discussed in Section 3.3.
1.4.4.1 Electrical Power Supply
Power supply standards are not set forth in this document.
COMMENTARY
The current philosophy of system and equipment design includes
provision of a power supply unit in each box. The original concept of
such power units was to provide a regulating interface between the
fluctuating voltage levels of the aircraft bus bars and the stabilized
requirements of the electronic equipment. Through evolution these
units have grown in complexity and scope and in modern equipment,
they provide a large variety of voltages from one input voltage level.
A survey conducted at the time of initial publication of this document
disclosed 50 different voltage levels in equipment on one aircraft. In
many instances voltage levels differed by as little as 0.1 volt. These
units are inefficient and the heat dissipated by them accounts for the
major proportion of heat dissipated by each box.
The standardization of voltage levels and the reduction or elimination
of power regulation within the boxes would reduce the heat
dissipation and so reduce the cooling problems. The research and
development on this part of ARINC 600 will consider provision of an
improved power supply for avionics, the reduction of power regulation
within boxes, the maintenance of integrity and reliability, and the cost
effectiveness to the airlines and to airframe and equipment
manufacturers. Benefits include reliability, cost effectiveness,
maintainability, shop capabilities, etc.
1.4.5
Wire Integration
An area should be provided on the rack or airframe structure for wire integration.
The aircraft wiring should interface with the LRUs through this area. The wire
integration area should be located to provide easy access to the wire which
connects the aircraft wiring to the electrical connectors on the rack. This
accessibility is needed to make changes to the wiring configuration and to make
repairs with minimum disturbance of the aircraft wiring.
1.4.6
Cooling Air Ducts and Plenums
Ducting and plenums are members built into the rack or mounted on adjacent
structure to direct the flow of cooling air through the LRU. Apertures in the top and
bottom surfaces of the LRU provide for passage of the cooling air through the unit.
LRUs must pass thermal appraisal tests with air flow either up or down.
ARINC SPECIFICATION 600 – Page 6
1.0 GENERAL CONSIDERATIONS
1.4.7
Standard International (S.I.) Units
All parameters should be expressed in Standard International (S.I.) units. A single
exception to this rule is in the dimensioning of contact center-to-center spacing in
multi-contact connectors. This dimension may be expressed as a decimal fraction of
an inch.
COMMENTARY
The contact centers and LRU spacing is retained on a 0.025-inch grid
in order to facilitate the use of semi-automatic or automatic wire
termination equipment. Because it is desired to retain a degree of
interchangeability with ARINC 404A equipment while converting to
metric nomenclature, linear dimensions have been rationalized rather
than making a hard conversion. S.I. units are shown first with the
U.S. customary equivalents in parenthesis. Conversions are in
accordance with International Standard ISO 1000 entitled “S.I. Units
and Recommendations for the Use of Their Multiples and of Certain
Other Units.” The term “weight” as used in this document means
mass as determined by a spring scale calibrated in mass units at a
local acceleration of free fall equal to 9.80665 meters per second
squared or by a beam balance. The unit used is the kilogram.
Conversion from S.I. (metric) dimensioning to imperial (inch)
dimensioning in this Specification has been done as a convenience to
the reader. It is the responsibility of the manufacturer to make the
necessary conversion from metric to inches to meet his own
manufacturing requirements, and accept whatever risk that carries if
he tightens or loosens tolerances beyond those provided.
1.4.8
Other Environmental Considerations
Unless otherwise specified herein, the environments specified in ARINC 404A apply
to equipment built to ARINC 600.
COMMENTARY
A major objective of ARINC 600 is to provide environmental
conditions for equipment that enhance reliability while minimizing
costs.
1.4.9
Related Documents
The latest version of the following documents applies:
ARINC Specification 404A: Air Transport Equipment Cases and Racking
RTCA DO-160/EUROCAE ED-14: Environmental Conditions and Test Procedures
for Airborne Equipment
International Standard ISO 1000: S.I Units and Recommendations for the Use of
Their Multiples and of Certain Other Units
ARINC SPECIFICATION 600 – Page 7
2.0 INTERCHANGEABILTIY
2.0 INTERCHANGEABILITY
2.1 LRU Interchangeability
Airlines desire that any LRU fabricated to ARINC 600 by one supplier be completely
interchangeable with an LRU performing the same function fabricated by another
supplier. While an installation using only ARINC 600 equipment is fundamental, this
Specification provides for an evolutionary change from existing ARINC 404A
installations through a hybrid installation that uses equipment fabricated to ARINC
404A and equipment fabricated to ARINC 600. Therefore, form factors compatible
with ARINC 404A units have been selected for ARINC 600.
2.2 Cabinets, Racks, and Shelves Interchangeability
The mechanical, electrical, and environmental interfaces between the rack or shelf
and the LRU (e.g., the electrical connector, cooling provisions, and attachment
method) are controlled by this Specification. However, racks and shelves designed
for one aircraft installation are not required to be interchangeable with other racks
and shelves, within that aircraft or with those of other aircraft.
COMMENTARY
Cabinets, racks, and shelves will, in most cases, be custom designed
to match the space available in a particular aircraft and the
environment (temperature, shock, vibration, and other environmental
factors) needs of the avionics. The design of the racks and shelves is
therefore, of necessity, the responsibility of the airframe
manufacturer. The racks and shelves must be designed to meet the
general requirements discussed in Section 3.2.
Racks and shelves must accommodate any manufacturer’s LRU designed to
perform a specified function, with complete mechanical, electrical, and
environmental interface compatibility. Furthermore, any ARINC 600 unit fabricated
by any supplier(s) to perform a standard function governed by an ARINC
Characteristic, must be suitable for installation in any racking system fabricated by
any airframe manufacturer whether built to this Specification or ARINC 404A. Units
fabricated to ARINC 404A cannot be plugged into an ARINC 600 rack.
To allow for hybrid designs where an ARINC 600 unit is installed in ARINC 404A
compatible rack, or where ARINC 404A boxes are to be installed in an aircraft
containing mostly ARINC 600 equipment, the following guidelines apply:
a. To retrofit in older aircraft racks, install an ARINC 600 backplate containing a
low insertion force connector per this Specification, thus allowing for the low
insertion force connector and complete electrical interface with the LRU. The
cooling system interface may require alteration to be compatible with the
equipment cooling system which exists in ARINC 404/404A type aircraft.
b. For airplane designs, where ARINC 404A boxes must be accommodated in
addition to ARINC 600 boxes, two rack-types may be provided:
1. One for ARINC 404A units that will accommodate ARINC 600 units.
2. One for ARINC 600 units exclusively.
ARINC SPECIFICATION 600 – Page 8
3.0 PHASE 1 DESIGN REQUIREMENTS
3.0 PHASE 1 DESIGN REQUIREMENTS
3.1 The MCU
The ARINC 600 Modular Concept Unit (MCU) is the basic building block module for
use in commercial airplane avionics system design. This specification provides for
the standard interfaces between ARINC 600 equipment and the electrical wiring,
environmental control systems, and supporting structures.
Internal configuration is the responsibility of the equipment supplier. However, in
addition to the specific limits of interfaces which are required for interchangeability,
precautions discussed in the following sections should be observed in internal
design.
3.1.1
Form Factor and Case Dimensions
The MCU is a right parallelepiped. The height and length dimensions are fixed.
Variations in LRU sizes (volume) are accounted for by modular increments in case
width. The smallest LRU is designated 1 MCU and others are designated nMCU
where n is the number of 1 MCU cases which would occupy the same shelf width as
the case in question. The dimensions associated with each case size are shown in
Attachment 2.
COMMENTARY
The MCU case sizes are derived from the short ATR boxes specified
by ARINC 404A which has been the industry standard for equipment
design. ARINC 600 Size 2, 3, 4, 6, and 8 MCU widths and tray
dimensions are identical to ARINC 404A. This form factor provides
for one way interchangeability as described in Section 1.2. ARINC
600 has a fixed height dimension rather than a maximum envelope
as in ARINC 404A. This allows design of a close-coupled cooling
system.
3.1.1.1 LRU Hold-Downs
A means of pushing the LRU connector into its mating rack connector, securing the
LRU on the shelf, and extracting the unit for removal is necessary. The LRU holddown mechanisms are defined in Attachments 2 and 7 of this document. The LRU
should have NAS 622 Type T (or functional equivalent) hold-down hooks installed
as shown on Attachment 7. The LRU should be capable of withstanding the
compressive forces exerted between the hold-down hooks on the front of the box
and the connector on the rear of the box, the vertical forces resulting from the
downward component of the hold-down devices, and the tensile forces resulting
from pulling the LRU out of its mating connector. The maximum values of the
compressive and tensile forces are as follows:
Table 3-1
Size (MCU)
Maximum axial force to be
applied by hold-down or
other insertion device.
1 and 2
560N (125 lbs)
3 through 12
1120N (250lbs)
Equally divided between
two hooks
Additional requirements of the LRU hold-down are as follows:
a. The front of the LRU must be securely held to the shelf.
ARINC SPECIFICATION 600 – Page 9
3.0 PHASE 1 DESIGN REQUIREMENTS
b. The LRU connector must be retained in the fully mated position with the
rack-mounted connector.
c. The attachment must absorb tolerances of shelf and LRU length as given in
Attachment 2.
d. Release and removal of an LRU with a failed hold-down should be readily
accomplished.
e. The hold-down force is limited by means supplied with the rack/cabinet. The
values of force exceed the contact insertion force by allowances for
misalignment of the LRU with the rack during initial engagement, location of
the box on the shelf, and securing of the hold-down devices.
Note: Although normally considered to be functionally equivalent to
the NAS 622 Type T hook, the NAS 622 Type E front holddown hook is not mechanically compatible with all LRU
insertion/extraction devices employed by the industry.
Therefore, equipment manufacturers should approach the use
of front hold-down devices other than NAS 622 Type T hook
with extreme caution.
3.1.1.2 Front Panel Protrusions
All protrusions such as hold-downs, carrying handles, switches, knobs, test
connectors, and indicators should lie within the outline envelope shown in
Attachment 2 when in the latched and actuated position.
3.1.1.3 Rear Panel
The primary purpose of the back of the LRU is for mounting the electrical connector.
Any other use should not interfere with the interfacing of the LRU with the rack.
Connector mounting screw heads must lie within the limits shown in Attachments 2
and 17. The rear mounting surface should have a maximum thickness of 2.5 mm.
The connector position on a LRU must be as specified in Attachment 3.
COMMENTARY
Projections on the LRU backplate surface are permitted, provided
there is no interference with the rack backplate. An example is the
use of sleeve type covers which are secured with screws or quick
disconnect fasteners (See Attachment 17, Note 4).
3.1.1.4 Maximum Weight
Maximum weight limits shown in Attachment 4 are assigned to enable adequate
structural design of racks and shelves which must carry the loads. In no case should
a unit having a weight of more than the amount given in Attachment 4 be installed. A
maximum weight of 20 kg is imposed on the largest LRUs for handling purposes.
See Commentary under Section 1.4.7.
3.1.1.5 Indexing
To guard against LRUs being inadvertently placed in the wrong rack location, a
standard means to index all LRUs must be provided. The indexing should be an
integral part of the connector as described in Section 3.3.2.
ARINC SPECIFICATION 600 – Page 10
3.0 PHASE 1 DESIGN REQUIREMENTS
3.1.1.6 Mating Force
The force permitted to slide the LRU along the shelf should not exceed 100N
(23 lbs). The connector engagement force on the LRU should not exceed the values
shown in Section 3.3.2.4.
COMMENTARY
This is actually a system requirement. The force required to slide the
LRU on the shelf is a function of the LRU weight, materials, and
finishes used on the LRU and shelf, gasket configuration, etc.
Therefore, in order to comply with this requirement, it will be
necessary to have knowledge of both the LRU and the shelf.
3.1.1.7 MCU Backplate Deflection
The backplate deflection during the period when the LRU is installed, is being
installed, or is being removed from the rack should be within the dimensions
specified in Attachment 2 (see Section 3.1.1.1 for the forces to be expected).
3.1.2
Vibration, Shock, and Acceleration
The interface between the LRU and the aircraft vibration and shock environment
should be via the base of the LRU, via the rear of the LRU, through the electrical
connector shelf, and via the front hold-downs. These same points will also provide
the reaction forces to hold the LRU under acceleration loads. While the vibration
and shock environment existing in a specific aircraft may be less severe than
shown, for the purposes of general design, the values shown in Attachment 13 may
be used. Today, regulatory bodies have authorized use of RTCA
DO-160/EUROCAE ED-14 for environmental testing.
3.1.3
Cooling
The cooling medium should be forced air (as described in Section 3.5.4) moving
through the LRU in the upward direction. The interface between the LRU and the
thermal environment provided by the electrical/electronic equipment cooling system
is via apertures located on the top and on the bottom surfaces of the LRU. Units
which do not require forced air cooling will not have opening on any surface. The
maximum permissible power dissipation for equipment not having cooling openings
is defined in Attachment 12.
COMMENTARY
Only if units can pass the thermal appraisal tests set forth in
Attachment 14 with no air at all may the manufacturer state that his
LRU requires no forced cooling air. The use of the term “convectioncooled” when referring to ARINC 600 LRUs is discouraged. Units not
requiring forced air cooling must pass appraisal test with no air
provided to the unit.
In all cases, the LRU designer must make efficient use of the cooling air supplied to
the unit. To this end, internal air distribution systems, baffles, heat exchangers, cold
plates, etc., should be judiciously employed to avoid hot spots. Particular attention
should be directed to avoiding air leaks that allow coolant to bypass heat transfer
surfaces.
ARINC SPECIFICATION 600 – Page 11
3.0 PHASE 1 DESIGN REQUIREMENTS
3.1.3.1 Cooling Air Interface
One interface with the equipment cooling system will be via the bottom surface of
the LRU. Therefore, the bottom surface of the LRU (Datum B, Attachment 2) must
be designed to minimize leakage. When possible, corners and sharp edges capable
of damaging sealing arrangements, if used, should be avoided.
The other interface with the cooling system is via apertures in the top surface of the
LRU. The top and bottom apertures must be confined to the zones indicated in
Attachment 9.
Cooling openings should be sized or screened to prevent falling debris from passing
through the interface. The maximum diameter of inlet and exhaust openings is
4.0 mm (0.157 in.). Other than at the top and bottom surfaces, there must not be
external openings since such openings will cause malfunctioning of the cooling
system.
COMMENTARY
Within the NIC Subcommittee, the desire for a top plenum was
expressed by some airlines to enable easy transition to a future
closed-loop cooling system. At the same time, some airframe
manufacturers foresaw problems in maintaining the height-tolerances
required between the shelf and such a top plenum.
3.1.3.2 Power Dissipation
The power dissipated within the LRU should be limited to the values shown in
Attachment 12. The quantity and condition of cooling air flow through the LRU is
described in Section 3.5.4. The pressure drop at the design flow rate from inlet to
exhaust must be 50 ±30 Pa (5 ±3 mm of water) for “Level 1” LRUs and 250 ± 50 Pa
(25 ±5 mm of water) for “Level 2” LRUs under standard conditions 101.3 kPa.
(1013.25 mbars). The methods used to manage heat flow within the unit and to
prevent temperature build-up at the power dissipating elements are not controlled by
this Specification. However, the results of that design should be proven in the
evaluation tests outlined in Section 3.5 and Attachment 14. See Section 3.5.4.5 on
cooling pressure drop.
3.1.4
LRU Evaluation
Each LRU design should be proved by Thermal Appraisal Tests per Attachment 14,
which demonstrates the unit’s capability to perform and survive under the conditions
set forth in this Specification.
3.2 The Equipment Rack/Cabinet
The term rack includes cabinet. An enclosed equipment rack with doors is defined
as a cabinet.
An equipment rack provides a method of installing a number of LRUs in any
particular location in the aircraft.
Individual shelves are used to provide a mounting platform for the equipment. The
equipment rack provides a means of interfacing the LRU with aircraft wiring,
equipment cooling system, and other equipment in the aircraft. Means must be
provided to collect exhaust air from each shelf mounted on a rack.
ARINC SPECIFICATION 600 – Page 12
3.0 PHASE 1 DESIGN REQUIREMENTS
Rack structure will vary depending on aircraft constraints such as available space,
equipment required, and mechanical considerations. The rack may be of open
construction, or it may be partially or entirely enclosed to meet specific
requirements.
The overall form factor of the rack will be optional to allow each airframe
manufacturer to best accommodate the required LRUs within the volume available.
The general arrangement of a typical rack assembly is shown in Attachment 1.
3.2.1
Datum and Method of Dimensioning
Dimensional control is established by use of datums which are physical features
from which other locations can be measured. Datums are as shown in
Attachment 5.
3.2.2
MCU Spacing on Rack Shelf
Shelves should be designed to accommodate the LRU guides.
The spacing between the LRU guides on a shelf is defined in Attachment 8. These
guides direct and position the LRU so that the connector on the rack or backplate
and the connector on the LRU will align for mating.
The spacing between the guide surface of one LRU guide and the adjacent guide
surface on the next LRU guide is shown in Attachment 6. The application of these
dimensions to a shelf is shown in Attachment 6.
For all LRU sizes and combinations of LRUs, the total assembled width of any other
group of LRUs, including spacing, is equal to the width of any other group of LRUs,
including spacing, having the same arithmetic sum of MCU-sized spaces.
COMMENTARY
The shelf spacing is selected to allow connector contacts to be
located on a 0.025-inch grid. Furthermore, interguide spacing and
LRU tray widths are equal. The use of the term “LRU guides” as
defined in Section 1.4.3 of this Specification as opposed to the term
“tray” as defined in ARINC 404 is not to imply trays cannot be used
as LRU guides, but is to imply an option is permitted at the discretion
of the airframe manufacturer to select either trays or rails as LRU
guides.
3.2.3
Mechanical Interface with the LRU
The ARINC 600 rack must be designed such that individual LRUs can be installed in
or removed from the rack without disturbing any other LRU. The rack must provide
the mechanical attachment points required by each LRU, i.e., the electrical
connector shell at the backplate, and the attachment points for hold-downs. The
location of old-down attachments should be as shown in Attachment 7.
COMMENTARY
There is no need to standardize the distance between shelves
beyond the minimum space required to clear maximum LRU height
“H.” The only critical dimension is to ensure that under all stress/load
conditions the distance between shelves exceeds the height of the
LRU. Individual rack designers will vary the distance between shelves
ARINC SPECIFICATION 600 – Page 13
3.0 PHASE 1 DESIGN REQUIREMENTS
depending on the space needed for cooling air ducts and electrical
wire bundles.
3.2.3.1 Backplate Assembly
The assembly of the backplate to the shelf tray or to the rack structure should be
designed to meet the tolerance requirements shown in Attachment 5.
3.2.3.1.1 Gauging of the Shelf Backplate
Gauging of the shelf backplate is considered essential to establish the
perpendicularity of the shelf connector mounting face relative to the plane of the
shelf load-bearing surface. A receiver-type gauge should be used.
3.2.3.1.2 Rack Backplate Deflection
The backplate deflection during the period when the LRU is installed, is being
installed, or is being removed from the rack should be within the dimensions
specified in Attachment 5 (see Section 3.1.1.1 for the forces to be expected).
COMMENTARY
One of the objectives of this Specification is to overcome the problem
of deflection forces applied to the rack due to high density electrical
connectors, thus the use of low insertion force connectors (see
Section 3.3). It must be recognized, however, that even with low
insertion force connectors, it is still necessary to apply some force to
engage the connector. The rack trays and backplates must be
designed to be compatible with these forces.
3.2.3.2 Front Retainer
The shelf, rack, or cabinet should provide a force-limiting, manually-operated,
means of pushing the LRU into its mating connector, means of holding the LRU in
place, and means for extracting the LRU from its connector. A protective barrier or
top shelf should be provided to prevent the front of an unlatched LRU being raised
more than 5 mm when being inserted in, or extracted from the rack.
3.2.3.2.1 LRU Hold-Down Details
The means for inserting and holding down the LRU to the shelf are as shown in
Attachment 7. The line of application of the insertion force should be inclined to the
horizontal as shown. The resultant horizontal component of the force applied by
each hold-down should be limited to the range of 450N to 560N by a mechanism
which prevents over-stressing the LRU. The interface of the LRU with the shelf/rack
hold-down is the NAS 622 T (or functional equivalent) hook. Forces on MCU 3
through 12 size LRUs are to be provided by two hold-down devices as shown on
Attachment 7. The resulting maximum forces on the LRU are as given in
Section 3.1.1.1.
COMMENTARY
Although normally considered to be functionally equivalent to the
Type T hook, the NAS 622 Type E front hold-down is not
mechanically compatible with all LRU insertion/extraction devices
employed by the industry. Equipment manufacturers should thus
approach the use of front hold-down devices other than the NAS 622
Type T with extreme caution.
ARINC SPECIFICATION 600 – Page 14
3.0 PHASE 1 DESIGN REQUIREMENTS
The inclined line of action provides a vertical component of holddown force to the LRU. The hold-down should absorb the tolerances
between the shelf and LRU length as given in Attachment 2. Full
engagement of the hold-down should be indicated by appropriate
means.
3.2.3.2.2 LRU Extractor Details
The shelf/rack/cabinet should provide an extractor mechanism which gives
mechanical advantage to assist in removing the LRU from the rack. The extractor
may operate against the front lip as shown on Attachment 2. The extractor should
conveniently apply forces as shown in the table below:
Table 3-2
Size (MCU)
Minimum Extractor
Force
1 and 2
560 N
(125 lbs)
3 through 12
1120 N
(250 lbs)
3.2.3.3 Mass of LRU Load
The shelves and racks must support the maximum mass per LRU shown in
Attachment 4. Design of the shelves and racks should take into account the
following:
a. The rack and shelf structures exhibit the minimum degree of independent
flexing of rack members under dynamic conditions when loaded with its full
compliment of LRUs (see Section 3.2.3).
b. The shelves should incorporate attachment points for front hold-down
devices to retain LRUs in position under dynamic conditions.
3.2.4
Electrical Bonding Interface
All metal parts of the rack and shelves should be maintained at airframe potential by
the application of suitable bonding and grounding techniques. The ground path
provided should be capable of conducting the maximum fault (short circuit) current
to which the rack may be exposed. Under such conditions, the resistance of the
ground path should not exceed 0.5 milliohms. The ground path should provide the
greatest surface area possible to allow a low impedance ground path for radio
frequency currents.
3.2.5
Environmental Interface Considerations
COMMENTARY
Regulatory requirements have been developed to assure satisfactory
performance by LRUs. It is recognized that the equipments and their
aircraft environmental interfaces came first and that regulation
followed when the design and practices leading to the high-quality
avionics performances were known. Current regulatory requirements
place severe environmental requirements on avionics equipment in
recognition of the historically poor environmental conditions actually
encountered by avionic equipment in aircraft prior to the approval of
ARINC 600. It is intended that ARINC 600 will bring about a change
in the environmental conditions as seen by the avionics LRU.
ARINC SPECIFICATION 600 – Page 15
3.0 PHASE 1 DESIGN REQUIREMENTS
It is a basic principle of ARINC 600 that the environmental conditions
encountered by avionics equipments are to be made much less
severe by providing a better aircraft installation and by control of all
significant environmental factors in the aircraft, not in the avionics
equipment. To this end, the airlines wish to place environmental
control in the most cost effective place so that a part of it will be in the
aircraft and some in the avionics.
With both aircraft and avionics being built to reduce the impact of
environmental conditions on avionics, RTCA/EUROCAE
environmental test documents will evolve.
Environmental control requirements in the following areas are
discussed in this section:





Vibration, shock, and acceleration
Thermal
Humidity
Contamination (chemical, physical, biological)
Altitude
3.2.5.1 Vibration, Shock, and Accelerations
The equipment racks, shelves, and trays should be designed to withstand the
vibration and shock encountered in all operating modes without damage to the rack
or to the equipment it contains. The rack should act as an attenuator of airframe
vibration modes and not as an amplifier. In addition, while the vibration, shock, and
acceleration environments existing in each aircraft are different, these interfaces will
have to accommodate and survive the environments set forth in Attachment 13.
3.2.5.2 Thermal Interface
The rack will serve as the interface between the electrical/electronic equipment
cooling system and the LRU. The racking should include ducting in each shelf so
arranged that the cooling medium can be delivered to and exhausted from the LRU.
Where supply ducting is assembled adjacent to, in contact with, or integral with the
return ducting, the aircraft designer is advised to make sure thermal resistance is
provided between them such that the thermal effect on the incoming coolant is kept
economically acceptable.
Prevention of loss of cooling air in the LRU is controlled by provisions at the
mechanical interface between the LRU and the shelf.
COMMENTARY
The interface designer must be sure that the shelf is so designed that
minimal damage will be caused to seals or other preventative
measures to preclude air loss by airline maintenance personnel in
inserting the LRUs in the shelf.
Metering plates should be used to control the air flow as required by each LRU (see
Section 3.5). The location and shape of the openings is as shown in Attachment 9.
ARINC SPECIFICATION 600 – Page 16
3.0 PHASE 1 DESIGN REQUIREMENTS
3.2.6
Equipment Rack Appraisal
The rack should be evaluated in accordance with the equipment rack appraisal
procedures defined in Section 3.7 to ensure that it meets the design criteria
established above.
3.2.7
Rack Maintenance and Accessibility
Easy access is required to allow the aircraft operators to perform maintenance and
modification work on wiring, wire integration, connectors, mechanical devices,
environmental control facilities, etc. The rack should be so designed that normal
hand tools may be used in maintenance and space for the use of those tools must
be adequate. Access is required to the back of the rack for removal and/or
maintenance involving the rear mounted connector.
3.3 The Rack and Panel Connector
The rack and panel connector used for equipment designed to meet this
Specification should utilize low insertion force technology. The low insertion force
rectangular connector is intended for use in the controlled environment of the
electrical/electronic bay area of the airplane. The connector should provide the
electrical and rear mechanical interface between the LRUs and the airplane
equipment rack.
COMMENTARY
The NIC Subcommittee spent considerable time on deliberations
around the ARINC 600 connector. For posterity reasons, it is
considered appropriate to list those considerations of connector
design which prompted these discussions. In the following
paragraphs, the considerations are listed in the chronological order in
which they were discussed and the commentary concludes with a
statement of the inference drawn from the deliberations.
In light of the ever-growing demand for more pins, transition from a
single DPA connector with 32 pins, to multiple connectors with
individual LRUs having in excess of 800 pins.
The high LRU insertion forces associated with these multiple
connectors introduced problems in maintaining the mechanical
tolerances necessary to ensure proper mating of rack mounted
connectors and so caused substantial problems in system reliability
and maintenance.
At first it was thought that the use of a Multi-Pin “Zero Insertion
Force” connector as used in other fields would provide the answer to
the problem. However, it then became clear that these connectors
required manually operated actuating devices. Airlines, having had
experience with actuating devices in connectors and in other
applications, were rather skeptical about the use of such devices;
however, recognizing the advantage of zero insertion force, they
were reluctant to altogether rule out the possibility of a manually
operated connector being acceptable.
The concern expressed about the use of actuators resulted in
creative thinking on how to do the same job without an external
actuator. This, in turn, resulted in various proposals which had in
ARINC SPECIFICATION 600 – Page 17
3.0 PHASE 1 DESIGN REQUIREMENTS
common the use of an overcam device in the connector, which
closed the contacts when the LRU was almost completely inserted in
the rack. Some force would be required to operate the overcam when
inserting and removing the LRU from the rack and this force would be
automatically provided by the action of inserting or removing the
LRU.
This connector was referred to as “self-actuating” or “automatic
actuating.” In addition, it became clear that manual, self, or
automatically actuated connectors would require a number of
conventional pin and sockets for power, co-axial, fiber optics, and
ground circuits. Consequently, reference to the connector was
changed from Zero Insertion Force to Low Insertion Force (LIF).
At this point in the deliberations, another candidate in the form of a
Medium Insertion Force (MIF) connector appeared on the horizon.
This was a connector currently in use outside the aviation industry
and it was demonstrated to have an insertion force of 200 N (44 lb)
for 600 pins. While the insertion force required for these connectors
was greater than that estimated for LIF connectors, it was considered
that their reliability would be greater than the latter because of the
simplicity of design, which does not involve actuators.
Table 3-3 – Summary of Connector Type Characteristics
NIC Subcommittee, San Francisco, October 1975
CONNECTOR
TYPE
HIF
MAN-LIF
AUTO-LIF
MIF
INSERTION
FORCE
(NEWTONS)
670
600 @ 4 oz.
calculated
(poor)
75
10 @ 4 oz.
590 @ 0.4 oz.
estimated
(very good)
150
10 @ 4 oz.
590 @ 0.8 oz.
estimated
(good)
200
600 @ 1.2 oz.
measured
(good)
NUMBER OF TYPES OF
CONTACTS
RELATIVE ESTIMATION OF
DESIGN FEATURES
MIF
Low
Contact
Resistance
Reliability
Overall
Simplicity
0
0
poor
not scored
very good
10
590
0
average
average
average
10
590
0
average
good
average
0
0
600
very good
good
very good
Conventional
ZIF
600
Although all three connector types discussed could fulfill the design requirements,
manufacturers were urged to direct their efforts towards designing a connector of
ARINC SPECIFICATION 600 – Page 18
3.0 PHASE 1 DESIGN REQUIREMENTS
high reliability and meeting the preferences expressed by the users. If these criteria
are applied to establishing an order of preference for connector type selection, then
based on Table 3-3 the order would be:
a. Medium Insertion Force (MIF) or auto actuated LIF connectors
b. Manually actuated (MAN-LIF) connectors
The rack and panel connector should meet the requirements of Attachment 19,
“Connector, Electric, Low Insertion Force, Rectangular.”
The Low Insertion Force Connector design should be applicable to LRUs which
employ the “open card” or “framed card” or “black box” approach to meeting the
dimensional requirements allocated for the specific space.
3.3.1
Connector Electrical Considerations
3.3.1.1 Contacts
The rack and panel connector should accommodate combinations of the following
contacts:
a. Low insertion force “signal” contacts with a 5 ampere, 115 Vrms continuous
duty rating.
b. Conventional power contacts to include sizes 8, 12, 16, and 20.
3.3.1.2 Deleted by Supplement 2
3.3.1.3 Electrical Circuits
The connectors should accommodate interfacing of electrical circuits ranging from 0
amps (dry circuits) to 50 amps. The low insertion force section should carry currents
up to 5 amps maximum on any one pin. Currents higher than 5 amps should be
carried by conventional pins and sockets.
3.3.1.4 Family of Connectors
The family of rack and panel connectors is shown in Attachment 19. The rows of
contacts should be numbered in accordance with Attachment 11.
COMMENTARY
This family has been selected as a result of analysis of usage on
current airplanes and requirements for digital equipment. The
smallest of the family was sized to accommodate a 1 MCU unit.
The family also takes into account the need to satisfy safety
requirements which dictate separated and multiple insert
configurations for circuit separation.
3.3.1.5 Shell
The shell of the connector must include provisions for physical barriers between
inserts required to satisfy circuit separation requirements. Contacts must not
protrude beyond the connector shell.
3.3.1.6 Inserts
Connector inserts should be individually replaceable in the field.
3.3.1.7 Intermateability
Connectors should be intermateable between manufacturers.
ARINC SPECIFICATION 600 – Page 19
3.0 PHASE 1 DESIGN REQUIREMENTS
COMMENTARY
This does not imply that inserts of different manufacturers must be
interchangeable.
3.3.1.8 Conntector-to-Wire Interface
The contact-to-wire interface designs must be compatible with the use of either
stranded or solid conductor wire including flat conductor cable. The electrical
contacts should be available with crimp barrels as well as rectangular posts.
Wire termination contacts are to be intermateable, interchangeable, and replaceable
between manufacturers.
Crimp contacts should be all rear release and rear removable. Contacts should be
positively retained by the insert.
The connector contacts must not be used as a switch to apply and remove power to
LRUs.
COMMENTARY
This means that some procedural method must be used to ensure
that power is removed before the LRU is installed in or removed from
the rack, e.g., the circuit breaker should be opened.
Actuated contact mating action should be designed to provide a wiped and backwiped surface contact. Wiping action should take place during the contact engage
sequence.
3.3.2
Connector Mechanical Considerations
The connector will serve as the mechanical interface between the rear of the LRU
and the equipment rack. Engagement of the connector contacts should be
automatically achieved through the action of inserting the LRU in the rack. The
connector shell should be designed to accommodate a LRU/Shelf lateral
misalignment of 2.5 mm (0.1 in.).
3.3.2.1 Shell Strength
The mated shells of the connector should be of sufficient strength to restrain the
LRU in position in all three axes when subjected to axial, vertical, and side loads
under all operating modes (2000 N or 450 lbs. approx.). This requirement assumes
that the hold-downs and latches used to restrain the front of the box are properly
latched and are also capable of meeting this three-axis requirement. The force
required to keep the connector halves mated should be provided by front mounted
position retainers (hold-downs).
3.3.2.2 Shell
The connector shell should act as a stop or limit for LRU insertion into the rack. The
shell must be designed to withstand forces of 4500 N (1000 lbs.).
3.3.2.3 Envelope and Configuration
The envelope and configuration of the connector is shown in Attachment 19.
ARINC SPECIFICATION 600 – Page 20
3.0 PHASE 1 DESIGN REQUIREMENTS
3.3.2.4 Engage and Disengage Forces
3.3.2.4.1 Future Designs
The force to fully engage and disengage the mated pair shells and contacts should
not exceed:



89 N (20 lbs.) for size 1
169 N (38 lbs.) for size 2
289 N (65 lbs.) for size 3
COMMENTARY
At the 1981 AEEC General Session held in Arlington, Virginia, AEEC
noted that Section 3.5.1 of Boeing Specification Control Drawing
SCD 10-61953 Revision G (see Attachment 19 to this document)
allows higher engage/disengage forces for all three shell sizes than
those stated above. The committee’s consensus, however, was that
ARINC 600 properly stated the air transport industry’s desires
concerning these forces and should not, therefore, be amended to
reflect the higher numbers.
3.3.2.4.2 Existing Designs
The first generation of connectors and components which were introduced into
service (before publication of Supplement 5 to ARINC 600) should fully engage and
disengage the mated pair of shells and contacts with a force not exceeding:



120 N (27 lbs.) for size 1
267 N (60 lbs.) for size 2
467 N (105 lbs.) for size 3
3.3.2.5 Moving Mechanism
If applicable, the connector half containing a moving mechanism should be in the
LRU.
3.3.2.6 Contact Actuator
If used, the contact actuator should be designed to preclude actuation of the
contacts until both connector halves are so positioned that actuation cannot cause
connector damage. Once the two connector halves have been mated, the forces to
maintain this engagement should be provided by hold-downs or latches located at
the front of the LRU. Similarly, the actuator must deactivate the contacts before
disengaging the connector shells. Intentional movement of the rear end of contacts,
except for normal float for engagement tolerance, is not permitted for contact
actuation.
The contact actuating device, if used, should be designed such that it cannot be in
the non-actuated position after it has been installed. The use of tools should not be
required for contact actuation or connector latching/unlatching.
3.3.2.7 Failure Mode
If actuating devices are used, the connector should fail only in the actuated position
to prevent circuit interruption, and should be so designed that the LRU can always
be removed with moderate effort and no tools if connector and/or actuator failure
occurs.
ARINC SPECIFICATION 600 – Page 21
3.0 PHASE 1 DESIGN REQUIREMENTS
3.3.2.8 Signal Contact
The signal contact center-to-center spacing is 0.100 inches on a 0.025-inch square
grid pattern. All other contacts should also be located on this same 0.025-inch
square grid pattern.
COMMENTARY
Much time has been devoted to discussion of the distance between
contacts. 0.150 inches has been advanced as being preferable
because of its compatibility with automated wire termination
techniques. However, 0.150 inches center-to-center leads to low
contact densities. Therefore, a 0.100 inch center-to-center spacing
has been specified.
3.3.2.9 Indexing Capability
The rack and panel connector shell must provide for indexing capability to ensure
that the LRUs are not inadvertently placed in wrong locations. The indexing will be
accomplished by means of integral keys and keyways.
The indexing devices should be located within the base of the connector shell (See
Attachment 19).
3.3.2.10 Index Numbering
Indexing of connectors should be numbered per Attachment 18. Each index position
shall be accomplished without disturbing the electrical contacts of the contact
portion.
3.3.2.11 Partial Contacts
The electrical performance, mechanical, and mateability of class A (unsealed)
connectors should not be degraded if only a partial complement of contacts is
installed.
COMMENTARY
It is not necessary from a mechanical integrity, electrical, or
mateability standpoint to install a contact in each contact cavity of an
ARINC 600 connector. However, consideration should be given to
cooling airflow paths (in forced air cooled units) when large numbers
of contact cavities are left unfilled.
3.3.2.12 Fiber Optic Termini
When designing an application, which uses ARINC 600 connectors and fiber optic
termini (excluding expanded beam types), the designer needs to perform a
complete analysis on the connector engagement forces and the effects. This
includes the forces for the fiber optic termini and the selected fiber optic cable. If the
connector engagement forces exceed those specified in the ARINC 600
specification, then the designer needs to ensure the LRU, avionics tray, LRU hold
downs, and any other components are designed to accommodate these forces.
COMMENTARY
ARINC 801 fiber optic termini and ARINC 802 fiber optic cables are
being used in an increasing number of applications on commercial
airplanes. Potentially on some of the new applications, the avionics
ARINC SPECIFICATION 600 – Page 22
3.0 PHASE 1 DESIGN REQUIREMENTS
racks may experience connector engagement forces exceeding those
currently specified in this document. The connector engagement
forces in many cases are still less than the forces applied by the LRU
hold-downs. This design guide will help the designer to limit potential
impact of these forces.
The traditional electrical contacts used in the majority of connectors today use the
pin and socket design. With the exception of the size one coax, contact engagement
forces are experienced during the connector engagement sequence and once this
sequence is completed there are no longer any contact engagement forces present
on the rack or hold downs.
The design of the fiber optic termini is different from the electrical contacts in that
the same terminus (contact) is used in both the plug and receptacle connectors. The
termini have polished faces and are mated together via a compressed butt joint. The
butt compression force is generated by a spring integral to each terminus. During
the connector engagement sequence the termini do not add to the engagement
forces until just prior to a fully-mated condition as the plug side termini enters the
alignment sleeve and the termini end faces mate and compress the springs. After
the connector mating sequence the termini forces remain because of the
compression between the termini. These spring forces are of concern and this
design guide will aid the designer in limiting these forces in their application. ARINC
Specification 801 describes the fiber optic termini and the associated spring forces.
The receptacle side contains the alignment sleeve which is shown in the figure
below.
Termini Endfaces
Physically Touch
Termini Ferrule
Alignment Sleeve
Termini Ferrule
Fiber Optic Termini Interface and Alignment
To reduce the forces due to fiber optic termini and cables, the designer should
consider the design guidelines in the following sections.
3.3.2.12.1 Cable Selection
The loose structure multimode (MGL) fiber optic cable allows the glass fiber core to
push back (buffer insertion force) as the fiber optic terminus is compressed. This
insertion force adds to the overall mating forces of the termini. When selecting a
fiber optic cable to use in the avionics rack and shelf area, the designer needs to
determine the buffer insertion force and choose a simplex cable with a low force. If a
duplex or other multiple conductor fiber optic MGL cable is used, the designer
should note that the buffer insertion force is higher than with a simplex type.
ARINC SPECIFICATION 600 – Page 23
3.0 PHASE 1 DESIGN REQUIREMENTS
3.3.2.12.2 ARINC 600 Connector Termini Layout
The avionics tray backplate will experience less deflection at the lower end of the
tray because of the stiffness. To take advantage of this feature, and where design
allows, populate the fiber optic termini in the lower ARINC 600 connector shell
cavities first. Below is a list of the connector shell sizes along with the insert cavities
and the order in which the termini should be populated (number 1 being first):
Note: Cavity C and cavity F (lower cavities) are commonly used for
power contacts. The designer should evaluate the
compatibility of fiber and power contacts in the same insert.
Shell sizes 1 and 2:
1. Insert cavity C (bottom insert)
2. Insert cavity B (middle insert)
3. Insert cavity A (top insert)
Shell size 3:
1. Insert cavities C and F (bottom inserts)
2. Insert cavities B and E (middle inserts)
3. Insert cavities A and D (top inserts)
3.3.3
Connector Environmental Considerations
The connector must accommodate and survive the environmental requirements
described in Attachment 13.
COMMENTARY
Rack and panel connectors should last the life of the aircraft (typically
100,000 hours operating time).
The rack and panel connectors should be available with and without
environmental protection. In those cases, in which the connector is
needed with environmental protection, the rack and panel connector
should be designed to have provisions to prevent moisture from
ingressing to the contacts either via the wire or at the connector to
the connector interface. Further, the connector must be designed to
prevent the ingress of sand, dust, or other contamination into the
connector when mated.
This consideration is important from two aspects, (1) the
contaminants can form films or layers on the contacts which create
high resistance paths in the contacts, (2) the contaminants could
lodge on critical moving surfaces which would restrict the degree of
movement of the moving member of the connectors.
3.3.4
Connector Tooling and Maintenance Consideration
3.3.4.1 Flight Line Tooling
All techniques and processes used to connect electrical wires to terminals used in
the connectors should be capable of being accomplished by a flight line technician
using inexpensive hand tools.
ARINC SPECIFICATION 600 – Page 24
3.0 PHASE 1 DESIGN REQUIREMENTS
3.3.4.2 Termination
Termination of the wire to the contact and of inserting contacts in the insert should
be compatible with automatic and semi-automatic installation techniques and must
be compatible with inexpensive hand tools.
COMMENTARY
While automated wire termination processes may become
economically justifiable for the airframe and equipment
manufacturers, they may not be justifiable for airline maintenance
operations. Therefore, any process which uses automatic or semiautomatic tools in the factory must be backed up by inexpensive and
easily operated hand tools and processes.
3.3.4.3 Manufacture Identification
All contacts and connector components must be marked permanently to identify the
manufacturer.
3.3.5
Connector Installation Considerations
3.3.5.1 The LRU Electrical Interface
The connector will serve as the electrical interface between the rear of the LRU and
the equipment rack. To ensure connector mateability the use of more than one
connector will not be permitted. Available connector types are shown in
Attachment 19.
The connector shell is installed on the inside surface (Datum A, Attachment 2) of the
back of the LRU and projects into but not through the opening in the rear of the
LRU. Connector mounting hardware must be within the limits shown in
Attachment 17 to avoid possible interference with the mating rack connector support
(see Section 3.3.5.2) function. Test requirements to be considered include airborne,
on-board, and shop. Where a dedicated connector is required for on-board and/or
shop testing it should be located on the front of the LRU. The connector type is to be
specified by the applicable ARINC Characteristic.
COMMENTARY
This requirement provides for both airborne and ground ATE
connections and may do away with many ATE connectors.
All electrical circuits inclusive of secondary ground connections will be via
connected contacts.
The impedance from any point of the LRU chassis to the connector shell when
measured at a direct current equivalent to the maximum supply current of the LRU
will not exceed 0.5 milliohms.
COMMENTARY
A secondary ground connection is defined as a circuit wire only
required to maintain a current path in unlikely failure of the main
primary ground.
A primary ground is defined as a ground providing the low impedance path
necessary to meet the requirements of Section 3.3.5.1.
ARINC SPECIFICATION 600 – Page 25
3.0 PHASE 1 DESIGN REQUIREMENTS
AC and DC supply input grounds should be routed through separate dedicated pins
in the LRU connector.
3.3.5.1.1 Connector Position
The connector position will be as shown in Attachment 3.
Close tolerance guides designed into the connector shell are used to accurately
position the connector on the MCU backplate (See Attachment 3 and Attachment
19). The locator bosses on the plane of the connector identified as Datum E control
the horizontal position. The location feet on the plane of the connector identified as
Datum B control vertical position.
The use of locator bosses permits replacement of a damaged connector in the field
with the same accuracy as achieved in the original factory installation and is not
dependent on accurately located connector mounting holes.
Connector cutout dimensions are given in Attachments 15 and 16.
Note: Use of the side mounting provisions for the shell size 1
connector is discouraged for rack and panel applications.
These mounting provisions do not include any form of locator
bosses, and it is not possible to design a cutout that will
interchangeably meet the 0.015 perpendicularity requirements
of Attachments 1 and 5, and the vertical location requirement
of Attachment 3.
3.3.5.2 The Rack/Cabinet Electrical Interface
The electrical interface between the rack/cabinet and the LRU should be
accomplished through a low insertion force connector mounted on the backplate of
the shelf or LRU guide. If applicable, the fixed half (or the non-actuated half) of the
connector should be attached to the backplate as shown in Attachment 5.
The connector shell is installed on the back surface (Datum E, Attachment 5) of the
backplate. Connector mounting hardware must be within the limits shown in
Attachment 17 to avoid possible interference with the mating LRU connector (see
Section 3.3.5.1).
COMMENTARY
The rack mounted connector flange is mounted differently from the
ARINC 404A practice of mounting the rack connector on the front
surface of the rack structure as determined by action of the NIC
Subcommittee at their May 2-5, 1977, meeting in Los Angeles. The
reasons advanced for this change as delineated as follows:
The major objections in order of priority to the back mounted
(backplate side the furthest from the MCU) connector as voiced by
the group were as follows in order of priority:
1. The airline maintenance personnel could not pull connector forward
for re-work.
2. Backplate damage due to high impact forces caused by MCU
insertion.
3. Connector flanges more susceptible to breakage due to high impact
forces caused by MCU insertion.
ARINC SPECIFICATION 600 – Page 26
3.0 PHASE 1 DESIGN REQUIREMENTS
The major objection to a front mounted (backplate side nearest the
MCU) connector is the difficulty encountered when installing a
connector, fully loaded with wires, to the front side of the backplate.
In some instances, using the DPX/MIL-C-81659 connector, it is
necessary to remove the inserts from the connector shell, push the
inserts through the backplate cutout and reinstall the shell. If the
inserts were not removed, the wires would have to be folded back
against the connector inserts and pushed through the backplate
cutout. Extreme care is mandatory to prevent wire damage and/or
splayed connector contacts.
Airframe manufacturers consider that to continue with a system
design which requires such practices is not in the best interest of the
industry and is not in consonance with the goal of increased reliability
established in ARINC 600. Therefore, the practice should be
discontinued.
Rather than penalize the wire bundle fabrication and installation
techniques to solve the problems outlined in items 2 and 3, it would
be more appropriate to design the connector shell and backplate to
withstand the high impact forces. Section 3.7 of ARINC 600 was
written to achieve that goal. The airframe manufacturers consider that
any arguments in favor of requiring a front mounted connector to
overcome insertion force problems are invalidated by the existence of
thousands of boxes which essentially use a back mounted connector
for the very same reasons that the airframe manufacturers wish to
use a back mounted connector on the rack. If a back mounted
connector is the weak link, the airframe manufacturers ask, why do
we continue to use this type of installation on the boxes?
With regard to the problem outlined in item 1, it is doubtful that a front
mounted connector can be pulled forward for re-work due to
insufficient bundle slack and the bundle ties. If sufficient slack is
provided, broken wires caused by vibration will be a problem. In
addition, the practice of pulling wire bundles forward for maintenance
is not considered to be consistent with reliability goals established by
the airlines.
If wire-wrap is used, moving connectors forward or twisting sideways
for re-work is not permitted as wire movement could break the gastight joint.
If the differences in connector mounting cannot be resolved (and this
is the third time around), then an alternative solution is to develop a
connector that can be either front mounted or back mounted. This
can be accomplished by designating the front face of the connector
mounting flange as Datum -E- (a fixed position). The back face of the
connector will be accurately dimensioned from the datum face (see
Attachment 19).
Variation in the connector mounting location affects only the position
of the backplate on the rack shelf (airframe manufacturer option). For
front mounted connectors, the backplate would be positioned aft of
ARINC SPECIFICATION 600 – Page 27
3.0 PHASE 1 DESIGN REQUIREMENTS
Datum -E-. The backplate would be positioned forward of Datum -Efor a back mounted connector.
This approach will have absolutely no effect on the LRU with respect
to its position on the shelf. Controlling dimensions are defined by
ARINC 600. The position of the backplate is determined by the
airframe manufacturer and/or system integrator.
3.3.5.2.1 Backplate Connector Positions
The connector position will be as shown in Attachment 3. Connector cutout
dimensions are given in Attachments 15 and 16 (refer to Section 3.3.5.1.1 for
description of connector mounting). The spacing between the connectors mounted
on the backplate is given in Attachment 6. The connector spacing is selected to
allow connector contacts to be located on a 0.025-inch grid (see Section 3.3.2).
Note: Use of the side mounting provisions for the shell size 1
connector is discouraged for rack and panel applications.
These mounting provisions do not include any form of locator
bosses, and it is not possible to design a cutout that will
interchangeably meet the 0.015 perpendicularity requirements
of Attachments 1 and 5, and the vertical location requirement
of Attachment 3.
3.3.5.2.2 Backplate Deflection
The perpendicularity requirements of Attachment 5 must be met when all equipment
is installed (see Section 3.2.3.1.2).
3.4 Wire Integration
Wire integration is a function rather than a specific separate item of hardware. It is
implemented as a part of the airframe wiring and the specific form it takes depends
largely on the wiring techniques employed by the airframe manufacturer. However,
there are some aspects of wire integration which the airlines wish to influence and
these are discussed below.
3.4.1
Mechanical Interface Consideration
3.4.1.1 Location of Integration Center
The wire integration center must be located on the rack of the airframe structure in
such a way that it is accessible for test, checkout, repair, removal, and retrofit
without removal of any other equipment or pieces of the airplane. If the rack is
located such that there is access to the rear or sides of the rack, the wire integration
center may be located there. If the back or sides of the rack are not accessible, the
wire integration center should be located in the front of, or remote from the rack.
3.4.1.2 Electrical Termination
The electrical terminations used for the wire integration center must be protected
from inadvertent contact with foreign materials and liquids which create unwanted
electrical circuits. An easily removable protective cover should be provided. Fluid
drainage should be provided.
3.4.1.3 Ease of Maintenance
Wire integration should not impede the ability to replace the connector on a rack
backplate. When a defective backplate connector is being replaced, there must be
ARINC SPECIFICATION 600 – Page 28
3.0 PHASE 1 DESIGN REQUIREMENTS
minimal disturbance of the circuits not directly associated with that connector,
(includes need for removal of adjacent LRUs).
3.4.1.4 Indexing
Connectors which are associated with wire integration must be indexed or keyed to
prevent inadvertent misconnection.
3.4.2
Electrical Interface Considerations
3.4.2.1 Non-Customization
The wire integration center should not use customized connectors and contact
systems.
3.4.2.2 Identification and Accessibility
Each circuit which goes through the wire integration center should be individually
identifiable and accessible so that it can be intercepted for repair, test,
reassignment, etc., with minimum disturbance to any other circuit.
3.4.2.3 Circuits Accommodation
The wire integration center should be designed to accommodate a mixture of
“straight through” circuits and “fanned out parallel” circuits.
3.4.2.4 Physical Barriers
The wire integration center should include provision for physical barriers required by
circuit separation.
3.4.2.5 Grounding
When the wire integration is accomplished on a separate removable unit, provision
should be made to ensure the proper grounding of circuits can be accomplished and
that, when there is a current of 10 amps DC, a voltage drop of less than 0.5 milivolts
between the ground part and structure is achieved.
3.4.3
Environmental Considerations
The wire integration hardware must meet the requirements of Attachment 13.
3.4.4
Tooling and Maintenance Consideration
All of the tooling and maintenance considerations of Section 3.3.4 apply to the wire
integration unit.
3.5 Thermal Management
3.5.1
Definitions
3.5.1.1 Electronic Part
An electronic part, for the purpose of this document, is defined as an item not
subject to further disassembly which is utilized in the fabrication of avionics
equipment. For example: resistors, capacitors, filters, circuit breakers, switches,
connectors, relays, coils, transformers, piezoelectric crystals, electron tubes,
transistors, diodes, microcircuits, waveguides, synchros, and resolvers.
3.5.1.2 Temperature Critical Parts
Temperature-critical parts are electronic parts, whose surface temperatures are
most likely to approach their maximum allowable temperature.
ARINC SPECIFICATION 600 – Page 29
3.0 PHASE 1 DESIGN REQUIREMENTS
3.5.1.3 Stabilization
A stabilized thermal condition has been attained when the indicated temperature of
all temperature sensors internal to the test chamber (including the instrumented test
unit electronic parts) have varied no more than 2 °C over a continuous two-hour
exposure period.
3.5.1.4 Maximum Steady State Heat Dissipation
Maximum steady-state heat dissipation is the condition wherein the equipment is
operated at the duty cycle which will yield the maximum heat dissipation (at rated
voltage level).
3.5.1.5 Ambient Temperature
Ambient temperature is the air temperature immediately surrounding the equipment
rack.
3.5.1.6 Thermal Design Condition
The thermal design condition is the environmental and electrical operating mode to
be used as the basic design condition for the equipment (not a worst-case
condition).
The thermal design condition represents normal ground operation of the equipment
as installed in the aircraft. For the test and design computational purposes herein,
the Thermal Design Condition is defined as follows:
a. Equipment in the steady state thermal condition (see Stabilization,
Section 3.5.1.3).
b. Equipment in the electrical operating mode which will yield the Maximum
Steady State Heat Dissipation.
c. Ambient pressure at 101.3 kPa (1013.25 mbar). The local ambient pressure
is acceptable provided it is noted in the test report.
d. Ambient temperature, except for variations caused by (e) below, at 50 °C.
e. Air velocities immediately surrounding the equipment not greater than those
caused by air movement due to natural (free) convection effects.
f. Coolant air bulk inlet temperature at 40 °C.
g. Coolant airflow rate at 220 kg/hr kW based on actual heat dissipation at
condition (b) above.
h. Inlet coolant air relative humidity not greater than 40%.
i. For test purposes, the equipment should be located in surrounding and
supporting structure which stimulates a standard for in-service usage
including adjacent units with surface temperatures of 60 ºC and minimum
emissivity’s of 0.85. (see Attachment 14).
3.5.2
Electronic Part Application
Note: This section is advisory in nature to caution the manufacturers
of avionics equipments regarding the problems associated
with electrical and electronic parts applications.
To achieve electro/thermal stress levels consistent with desired performance and
reliability, electronic part temperature should be limited as follows:
ARINC SPECIFICATION 600 – Page 30
3.0 PHASE 1 DESIGN REQUIREMENTS
a. Electronic part temperatures for any anticipated operational mode should not
exceed the component manufacturer’s absolute maximum operating curve.
This temperature limit is usually expressed as a function of power dissipation
but it may be a function of voltage, current, or other parameter of operation
or combination thereof. Anticipated operational modes include the startup
transient following a high temperature soak, the high continuous operating
temperature, and continuous operation at reduced coolant flow rate (see
Sections 3.5.3 and 3.5.4). It is expected that all of these conditions may be
encountered during the equipment lifetime but they do not represent normal
operations and therefore are not the basis for a conventional reliability
assessment. However, the probability of occurrence is considered high
enough that electronic parts should be able to survive these operating
conditions without a drastic reduction of equipment life (as would be
expected to occur when the component manufacturer’s absolute maximum is
exceeded).
b. During normal ground operation of equipment, defined by the thermal design
condition (see 3.5.1.6), Electronic Part temperature should not exceed a limit
determined by the reliability number apportioned to that part based on the
reliability number assessed against the equipment. MIL Handbook 217 will
be used as the basis of determination that the applied electrical stresses and
the maximum predicted part temperature are in accordance with the
reliability apportionment for the part (It should be noted that “part
temperature” actually means part surface temperature and that
measurement or calculation should relate to surface temperatures and not
internal operating temperatures).
COMMENTARY
The maximum predicted part temperature must also take into account
the effect of temperature of adjacent parts as well as the ambient air.
It is no good to calculate the maximum predicted power/operating
temperature of, say, a transistor based on the apportionment and
then placing it physically next to a wire wound resistor whose
maximum predicted power/operating temperature is also based on
the reliability data for that resistor. Either the maximum power
dissipated by the transistor should be de-rated to take into account
the ambient created by the resistor or the resistor should be rerated
to create an environment which does not have a deleterious effect on
the transistor.
3.5.3
Ambient Temperature
This is the ambient air temperature immediately surrounding the equipment rack.
For test purposes, ambient temperature is measured 75 mm in front of the LRU.
a. Ground Survival Temperature
-55 °C to 86 °C
Note: These are the lowest and highest ground temperatures
expected to be experienced by equipment during aircraft
storage or exposure to climatic extremes with power off.
Equipment is not expected to be capable of operation at these
temperatures, but to survive them without damage.
ARINC SPECIFICATION 600 – Page 31
3.0 PHASE 1 DESIGN REQUIREMENTS
b. Short Term Operating Temperature, Thirty Minutes Duration
-40 °C to 70 °C
Note: These are startup conditions where equipments are turned on
immediately following a ground soak. It is expected that these
conditions will be of short duration since cooling or heating air
circulation or other means of controlling compartment
temperature would be enabled concurrent with (or preferably
preceding) avionics equipment startup.
c. Low and High Operating Temperature, Ground or Flight
-15 °C to 65 °C
d. Normal Ground Operating Temperature
50 °C
Note: This is the design temperature (see Section 3.5.1.6, Thermal
Design Condition) to be used in analysis of electrical
component derating in accord with the guide lines given in
Section 3.5.2.
3.5.4
Coolant Air
Coolant air applied to LRUs installed in racks in an airplane should be as follows:
3.5.4.1 Coolant Air, Bulk Temperature at the LRU Inlet, Minimum to Maximum
a. Short-time operation, equipment startup, thirty minutes (30) duration.
-40 °C to 70 °C
b. Continuous ground or flight operation
-15 °C to 55 °C
c. Normal continuous ground operation, See Section 3.5.1.6, Thermal Design
Condition
40 °C
Note: This is the design temperature selected for electrical
component derating in accord with the part application
guidelines of Section 3.5.2.
d. Normal continuous flight operation
30 °C
3.5.4.2 Coolant Air Relative Humidity
The coolant air should contain no droplets of condensate.
3.5.4.3 Coolant Air Flow Rate
Cooling air is to be supplied to each equipment in proportion to the equipment’s
steady state heat dissipation, defined in Section 3.5.1.4. The design air flow rate
should 220 kg/hr kW at sea level.
When the inlet cooling air temperature can be reduced, in ground or flight operation,
the airflow rate can be expected to be reduced proportionally down to a minimum
airflow rate of 136 kg/hr kW at a coolant air inlet temperature of 30 °C.
ARINC SPECIFICATION 600 – Page 32
3.0 PHASE 1 DESIGN REQUIREMENTS
3.5.4.4 Coolant Air Quality
The cooling air must not contain contaminant particles in excess of 400 microns. A
centralized air cleaning system is acceptable to meet this requirement.
COMMENTARY
Experience has shown that contaminated air degrades cooling and
has an impact upon performance and is detrimental to the life of
electronic equipment.
3.5.4.5 Coolant Air Pressure Drop through the Equipment Level 1 and Level 2
The coolant air pressure drop through the equipment should be between 50 ± 30 Pa
(5 ± 3 mm of water) for “Level 1” LRUs and 250 ± 50 Pa (25 ± 5 mm of water) for
“Level 2” LRUs at the Section 3.5.4.3 flow rate. When internal blowers are used, the
flow resistance should exceed the above limits. In some special cases an internal
blower may decrease the flow resistance to zero or blow, causing reduced airflow
through other equipment. This should not be permitted to exist except intermittently
(i.e., not to exceed 30 seconds each two minutes). This pressure drop does not
include the drop through a metering orifice when such orifice is located external to
the equipment case; e.g., in a rack mounted equipment tray (For test purposes, at
laboratory ambient pressure other than 101.3 kPa corrections are allowed; see
Attachment 14, Section 14.4, Step 5.).
COMMENTARY
For contamination-sensitive units where indirect cooling is necessary,
a higher-pressure drop may be required. Under such conditions, the
excess pressure drop must be offset internally. An internal fan may
be used for this purpose. It cannot be assumed that the rack can be
modified to provide sufficient flow to a unit with excessive pressure
drop.
The use of internal blowers in equipment is not encouraged. When
blowers are provided to meet the needs of non ARINC 600 cooled
installations, blower power should be wired through a separate pin on
the rear connector. When such equipment is used in ARINC 600
cooled installations, the tray orifice should be sized to allow the
standard airflow rate and power normally should not be provided for
the blower.
3.5.4.6 Coolant Air Inlet and Outlet Locations
The coolant air should enter the equipment through the bottom and exit through the
top surface only. This can be accomplished by blowing or sucking the air.
COMMENTARY
Thermal appraisals for both upward and downward flowing cooling
medium are included in order to assure that equipment manufactured
to this Specification can be installed in an ARINC 404A rack in
accordance with the ground rule for one way interchangeability
between ARINC 600 equipment and ARINC 404A racks. See
Section 1.2.
ARINC SPECIFICATION 600 – Page 33
3.0 PHASE 1 DESIGN REQUIREMENTS
3.5.4.7 Coolant Air Leakage from the Equipment
There should be no air paths into or out of the equipment other than the bottom and
the top of the units. Parasitic leakage must be minimized.
3.5.5
Equipment Sidewall Temperature
Under the thermal design conditions specified in Section 3.5.1.6 (i), the average
temperature of any equipment vertical sidewall (including front and back vertical
surfaces) should not exceed 60 °C. There should be no sidewall hot spot
temperatures in excess of 65 °C.
3.5.6
LRU Thermal Appraisal
The LRU should meet the minimum standards of thermal design defined in
Attachment 14. This may be demonstrated by means of a thermal appraisal
intended to show that temperatures remain within the limits set forth in
Attachment 14.
3.5.6.1 Identification and Data Tabulation for Heat Dissipating and Temperature Critical
Parts
In order to ensure that the thermal design is adequate, an equipment manufacturer
may wish to determine and record the following (or equivalent) data concerning
temperature critical components prior to conducting a thermal evaluation test:
a. Description Identification of the part type should be presented under a
column headed “description”; e.g., RL07 resistor, 2N2484 transistor, IN746
diode, CKR05 capacitor, etc. The term part should include encapsulated
assemblies.
b. Schematic Identification The tabulated data should include the schematic
symbol for each part; e.g., R106, Q127, V701, etc.
c. Location A general description of the location of the part should be provided.
d. Manufacturer’s maximum rated operating dissipation may be the absolute
maximum recommended by the part manufacturer or may be some upper
limit less than the absolute maximum operating dissipation established by
the equipment manufacturer.
e. Heat dissipation is the value for the rate of energy, in watts, being dissipated
by the part during operation at the thermal design condition (as defined in
Section 3.5.1.6). Preferably this value should be the result of measured data,
but it may be determined through calculations.
f. Maximum Surface Temperature (TM) This is the absolute maximum surface
temperature allowable in the above, (e.), mode of operation as determined
by the component manufacturer’s specification.
g. Design Surface Temperature (TC) The design surface temperature is
defined as the maximum external surface temperature that can be tolerated
consistent with the part’s function and system or equipment specified
reliability requirement at the Thermal Design Condition. The value for this
temperature and its location on each part should be tabulated for each part.
For electrical parts, the Design Surface Temperature should be determined
as outlined in Section 3.5.2 (b), Electronic Part Application.
Note: Parts which are encapsulated assemblies of basic component
parts should have their maximum and design surface
ARINC SPECIFICATION 600 – Page 34
3.0 PHASE 1 DESIGN REQUIREMENTS
temperatures tabulated. The thermal relationship between the
parts in the encapsulation and the encapsulated assembly
surface should be reported in sufficient detail to allow the
prediction of the internal part temperatures from the measured
encapsulated assembly surface temperature.
3.5.6.2 Thermal Evaluation Test
A Thermal Evaluation Test should be conducted on one representative production
unit in accordance with the procedures of Attachment 14. The evaluation should
determine for operation at elevated temperature (1) the equipment total heat
dissipation, (2) the pressure drop versus air flow relationship, and (3) the
temperature of equipment sidewalls and selected internal parts.
The LRU design should meet or exceed the minimum standards of thermal
performances set forth in Attachment 14 when tested in an upward or downward
coolant airflow environment as prescribed by Section 14.4.
Thermal Appraisal tests are also included for units not requiring forced air cooling, in
order to ensure that the equipment can operate properly and not have a detrimental
effect on surrounding units.
COMMENTARY
Thermal appraisals for both upward and downward flowing cooling
medium are included in order to assure that equipment manufactured
to this Specification can be installed in an ARINC 404A rack in
accordance with the ground rule for one way interchangeability
between ARINC 600 equipment and ARINC 404A racks (see
Section 1.2). ARINC 600 equipment may also receive downward
airflow cooling when installed in a rack since the airplane cooling
system may switch to a reverse cooling mode during certain smoke
removal and emergency operating conditions.
3.5.7
Thermal Interface Information
The following information should be supplied with the Equipment Installation and
Control Drawing:
a. Total wattage input and actual heat dissipation for all modes of electrical
operation for which the equipment was designed; e.g., standby, receiving,
transmitting, etc.
b. Estimated in-flight and ground maximum duty cycle (when specified in the
ARINC Characteristic)
c. Pressure drop through the unit in mm of water when the inlet coolant
pressure is 101.3 kPa, and
1. Coolant inlet temperature is 40 °C at a flow rate of 220 kg/hr kW.
2. Coolant inlet temperature is 30 °C at a flow rate of 136 kg/hr kW.
d. Average temperature of equipment sidewalls at the Thermal Design
Condition
e. Effect of dry contamination on unit cooling performance and recommended
unit service intervals required to maintain cooling performance, if applicable
ARINC SPECIFICATION 600 – Page 35
3.0 PHASE 1 DESIGN REQUIREMENTS
3.6 Power Quality and Power Conditioning
An electrical interface section is included in this Specification to provide guidance
information to the equipment engineer regarding:
a. The characteristics of the aircraft electrical power available to the LRU at the
equipment rack
b. Conversion and conditioning of this power for use within the LRU
3.6.1
Power Quality
The characteristics of the electrical power supplied to the equipment racks are
usually specified by the airframe manufacturer for a particular aircraft. The
specification describes the limits of deviation of the power quality from nominal
under steady state, normal, abnormal, and emergency conditions of operation in the
aircraft electrical system.
Each aircraft electrical power quality specification may vary slightly with regard to
specific parameter being observed and values assigned to that parameter under
various operating conditions. However, it is generally accepted that, in the vast
majority of aircraft, no problems due to input power quality will be encountered by
LRUs/Equipment which have been designed to meet the Category A requirements
for Power Input Tests and Voltage Spike Conducted Tests of RTCA DO-160,
Environmental Conditions and Test Procedures for Airborne Equipment.
Therefore, for the purpose of this Specification, the electrical power interface at the
equipment rack will be considered as defined by the latest version of RTCA
DO-160/EUROCAE ED-14.
3.6.2
Power Conditioning
All conversion and/or conditioning of power to obtain desired frequency, level of
voltage, or quality of power will be accomplished within the LRU or by the
subsystem of which the LRU is part. Care should be taken in the design of the
power conditioning section to minimize the thermal losses, and to control the effect
of conducted and radiated interference.
3.7 Mechanical and Structural Appraisals
The ARINC 600 rack manufacturer should show by analysis or test that the rack will
meet the deflection and bending requirements under specified conditions of load,
and that the rack has the required strength to resist all operational stresses.
The airplane cooling system should be tested to demonstrate that the required
airflow rates are achieved at the specified inlet temperatures.
The LRU manufacturer should show by analysis or test that the unit meets required
weight, vibration, shock, and acceleration load limits.
a.
b.
c.
d.
Conventional coaxial contacts as required in MIL C-81659A
Fiber Optic contacts
Liquid contacts
Pneumatic contacts
ARINC SPECIFICATION 600 – Page 36
ATTACHMENT 1
TYPICAL RACK ASSEMBLY
ATTACHMENT 1
TYPICAL RACK ASSEMBLY
ARINC SPECIFICATION 600 – Page 37
ATTACHMENT 2
STANDARD LRU CASE SIZE
ATTACHMENT 2
STANDARD LRU CASE SIZE
ARINC SPECIFICATION 600 – Page 38
ATTACHMENT 2
STANDARD LRU CASE SIZE
Case Dimensions:
Standard
LRU Sizes
1
2
3
4
5
6
7
8
9
10
11
12
Dimension W (millimeters)
Minimum – Maximum
25.15 – 25.65
56.64 – 57.66
89.92 – 90.94
123.44 – 124.46
156.72 – 157.74
190.00 – 191.02
222.76 – 223.78
255.78 – 256.80
288.80 – 289.82
321.82 – 322.84
354.84 – 355.86
387.86 – 388.88
Dimension W (inches)
Minimum – Maximum
0.990 – 1.010
2.230 – 2.270
3.540 – 3.580
4.860 – 4.900
6.170 – 6.210
7.480 – 7.520
8.770 – 8.810
10.070 – 10.110
11.370 – 11.410
12.670 – 12.710
13.970 – 14.010
15.270 – 15.310
Zone A Minimum Widths (centered on datum plane W):
Connector
Size
Dimension M
(millimeters)
Dimension M
(inches)
1
2
3
25.65
45.97
83.06
1.010
1.810
3.270
Attachment 2 Notes:
1. All dimensions and tolerances are in millimeters (inches).
Dimensioning and tolerance is in accordance with ASME Y 14.5M –
1997. Orthographic views are third angle projection.
2. A maximum LRU rear panel thickness of 2.54 mm (0.100 inch) is
required in Zone A for the front flange mounting method. For front
flange mounting, Datum A is the interior (front) surface of the LRU
rear panel wall. For rear flange mounting, Datum A is the exterior
(rear) surface of the LRU rear panel wall.
3. No features or other intrusions, except for connector mounting
hardware, are permitted in Zone A for both front and rear flange
mounting methods.
4. The intersections of features W and surface B shall clear a maximum
radius of 1.27 mm (0.050 inch) when placed in the shelf/rack
assembly.
5. Perpendicularity tolerance for width W is required only for the first
19.05 mm (0.750 inch) above datum B. Perfect form at Maximum
Material Condition for remaining height is not required.
ARINC SPECIFICATION 600 – Page 39
ATTACHMENT 2
STANDARD LRU CASE SIZE
Optional Forward Projections at the Front Panel of the LRU:
63.5 mm
[2.50 in]
MAXIMUM
See Note 7
F
FRONT VIEW
SIDE VIEW
B
FRONT PANEL MAXIMUM WIDTH:
DIM. W MAX + 4.06 mm [0.160 in]
See Note 7
Attachment 2 Notes (continued):
6. All protrusions (such as hold downs, carrying handle, switches,
knobs, test connectors, and indicators) will lie within the outline
envelope shown above, when in the latched position.
7. The dimensions above are absolutes, including any coatings,
finishes, platings, or fasteners.
8. Drawings updated by Supplement 11.
ARINC SPECIFICATION 600 – Page 40
ATTACHMENT 3
LOCATION OF CONNECTOR
ATTACHMENT 3
LOCATION OF CONNECTOR
Note: Drawing updated by Supplement 13.
Front View of Shelf / Rack:
(2X 4.67 - 4.78 [ .184 - .188])
0.38 [ .015] K T
0.25 [ .010] K
(CONNECTOR PLUG SHELL)
(GUIDES)
1 THROUGH 12 MCU
GRID CENTERLINE
(DATUM PLANE T)
0.05
[.002]
K
S
DIM. T
(see Attachment 8)
T
0.1 [ .004 ] K
Rear View of Unit:
(2x 4.67 - 4.78 [ .184 - .188 ])
0.64 [ .025] B W
0.25 [ .010] B
1 THROUGH 12 MCU
GRID CENTERLINE
(DATUM PLANE W)
(CONNECTOR RECEPTACLE SHELL)
0.13
[.005]
H
(see Attachment 2)
DIM. W
0.26 [ .010 ] B
B
W
ARINC SPECIFICATION 600 – Page 41
ATTACHMENT 4
MAXIMUM LRU WEIGHT
ATTACHMENT 4
MAXIMUM LRU WEIGHT
LRU CASE SIZE
1 MCU
2 MCU
3 MCU
4 MCU
5 MCU
6 MCU
7 MCU
8 MCU
9 MCU
10 MCU
11 MCU
12 MCU
MAX. PERMISSIBLE
WEIGHT KG
2.5
5.0
7.5
10.0
12.5
15.0
17.5
20.0
20.0
20.0
20.0
20.0
MAXIMUM WEIGHT OF LRU
Note: See Commentary under Section 1.4.7 regarding
measurement of weight and mass.
ARINC SPECIFICATION 600 – Page 42
ATTACHMENT 5
SHELF/RACK DATUMS
ATTACHMENT 5
SHELF/RACK DATUMS
(CONNECTOR)
(BACKPLATE)
1 THROUGH 12 MCU GRID CENTERLINE
(DATUM PLANE T)
DIM. T
T
0.38 [ .015] K T
TOP VIEW
E
(GUIDES)
K
FRONT VIEW
(SHELF)
SIDE VIEW
Attachment 5 Notes:
1. The surface area of the backplate defined as datum E is confined to
each connector mounting area individually.
2. Drawings updated by Supplement 11
ARINC SPECIFICATION 600 – Page 43
ATTACHMENT 6
STANDARD SHELF DATUM LINE GRID AND LRU LOCATIONS
ATTACHMENT 6
1 MCU
1
STANDARD SHELF DATUM LINE GRID AND LRU LOCATIONS
2 MCU
1
3 MCU
1
5 MCU
1
4 MCU
1
6 MCU
1
16.51 MM
(.650 IN.)
(TYP)
1
CONNECTOR LOCATER BOSSES SHOULD BE POSITIONED ON GRIDS AS INDICATED
FOR VARIOUS SIZES OF MCU'S.
ARINC SPECIFICATION 600 – Page 44
ATTACHMENT 7
LRU HOLD DOWN MECHANISMS
ATTACHMENT 7
LRU HOLD DOWN MECHANISMS
ARINC SPECIFICATION 600 – Page 45
ATTACHMENT 7
LRU HOLD DOWN MECHANISMS
Note: Drawings updated by Supplement 11.
ARINC SPECIFICATION 600 – Page 46
ATTACHMENT 8
SHELF/RACK DIMENSIONS FOR LRU GUIDES
ATTACHMENT 8
SHELF/RACK DIMENSIONS FOR LRU GUIDES
1 THROUGH 12 MCU
GRID CENTERLINE
(DATUM PLANE T)
CR 1.27 [.050]
MAXIMUM
19.05
[.750]
MAXIMUM
(GUIDES)
K
(SHELF / RACK)
DIM. T
T
0.64 [ .025] M K
Dimension T Minimum - Maximum
LRU Size
(millimeters)
(inches)
1 MCU
27.94 – 28.19
1.100 – 1.110
2 MCU
60.45 – 60.96
2.380 – 2.400
3 MCU
93.47 – 93.98
3.680 – 3.700
4 MCU
127.00 – 127.51
5.000 – 5.020
5 MCU
160.2 – 160.53
6.300 – 6.320
6 MCU
193.04 – 193.55
7.600 – 7.620
7 MCU
226.06 – 226.57
8.900 – 8.920
8 MCU
259.08 – 259.59
10.200 – 10.220
9 MCU
292.10 – 292.61
11.500 – 11.520
10 MCU
325.12 – 325.63
12.800 – 12.820
11 MCU
358.14 – 358.65
14.100 – 14.120
12 MCU
391.16 – 391.67
15.400 – 15.420
ARINC SPECIFICATION 600 – Page 47
ATTACHMENT 8
SHELF/RACK DIMENSIONS FOR LRU GUIDES
Note: Drawing updated by Supplement 11.
ARINC SPECIFICATION 600 – Page 48
ATTACHMENT 9
COOLING APERTURES
ATTACHMENT 9
COOLING APERTURES
Attachment 9 Notes:
1. Exhaust area outlet openings must be at the top surface only.
2. Maximum diameter of individual inlet and exhaust openings shall be
4.06 mm [0.160 inch].
3. Attachment 9 drawings updated by Supplement 11.
ARINC SPECIFICATION 600 – Page 49
ATTACHMENT 9
COOLING APERTURES
ARINC SPECIFICATION 600 – Page 50
ATTACHMENT 9
COOLING APERTURES
ARINC SPECIFICATION 600 – Page 51
ATTACHMENT 10
DELETED
ATTACHMENT 10 DELETED
Deleted upon reorganization of Attachment 19 by Supplement 5.
ARINC SPECIFICATION 600 – Page 52
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
ATTACHMENT 11 CONTACT POSITION IDENTIFICATION AND INSERT SIZE
1
2
3
Figure 11-1 – Arrangement 01, Shell Size 1
1
2
3
Figure 11-2 – Arrangement 03, Shell Size 1
ARINC SPECIFICATION 600 – Page 53
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
1
2
3
Figure 11-3 – Arrangement 02, Shell Size 2 and 3
Applicability
Shell Size: 2 and 3
Insert:
Upper & Middle
38.79
(1.527)
Contact Configuration
Type:
Size 1 Coax
Quantity: 2
1
2
3
26.34
(1.037)
Figure 11-4 – Arrangement 09, Shell Size 2 and 3
ARINC SPECIFICATION 600 – Page 54
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
1
2
3
Figure 11-5 – Arrangement 05, Shell Size 2 and 3
1
2
3
Figure 11-6 – Arrangement 08, Shell Size 2 and 3
ARINC SPECIFICATION 600 – Page 55
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
1
2
3
Figure 11-7 – Arrangement 07, Shell Size 2 and 3
1
2
3
Figure 11-8 – Arrangement 10, Shell Size 2 and 3
ARINC SPECIFICATION 600 – Page 56
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
1
2
3
Figure 11-9 – Arrangement 04, Shell Size 2 and 3
1
2
3
Figure 11-10 – Arrangement 11, Shell Size 2 and 3
ARINC SPECIFICATION 600 – Page 57
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
1 Position Insert as
shown in Figure 11-26
Figure 11-11 –
Arrangement 29
2 Position Insert as
shown in Figure 11-26
Figure 11-12 –
Arrangement 30
Notes:
1.
2.
3.
4.
5.
Accommodates mini-expanded beam inserts
All are shell size 1 “signal” cavity “A” or “B”
All views are mating face
Cavity centerline at location 0.00, 0.00
Drawings updated by Supplement 13
3 Position Insert as
shown in Figure 11-26
Figure 11-13 –
Arrangement 31
ARINC SPECIFICATION 600 – Page 58
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
Tandem Insert as
shown in Figure 11-26
Figure 11-14 –
Arrangement 32
1 Position Insert as
shown in Figure 11-26
Figure 11-15 –
Arrangement 33
Notes:
1.
2.
3.
4.
5.
Accommodates mini-expanded beam inserts
All are shell size 1 “signal” cavity “C”
All views are mating face.
Cavity centerline at location 0.00, 0.00
Drawings updated by Supplement 13
2 Position Insert as
shown in Figure 11-26
Figure 11-16 –
Arrangement 34
ARINC SPECIFICATION 600 – Page 59
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
1 Position Insert as
shown in Figure 11-26
2 Position Inset as
shown in Figure 11-26
Figure 11-18 –
Arrangement 36
Figure 11-17 –
Arrangement 35
3 Position Insert as
shown in Figure 11-26
Figure 11-19 –
Arrangement 37
Notes:
1.
2.
3.
4.
5.
Accommodates standard-expanded beam inserts.
All are shell size 2 or 3 “signal” cavity “A,” “B,” “D,” or “E”
All views are mating face, receptacle side.
Cavity centerline at location 0.00, 0.00
Drawings updated by Supplement 13
ARINC SPECIFICATION 600 – Page 60
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
Tandem Insert as
shown in Figure 11-26
Figure 11-20 –
Arrangement 38
1 Position Inset as
shown in Figure 11-26
Figure 11-21 –
Arrangement 39
2 Position Insert as
shown in Figure 11-26
Figure 11-22 –
Arrangement 40
Notes:
1.
2.
3.
4.
5.
Accommodates standard-expanded beam inserts
All are shell size 2 or 3 “power” cavity “C” or “F”
All views are mating face, receptacle side
Cavity centerline at location 0.00, 0.00
Drawings updated by Supplement 13
ARINC SPECIFICATION 600 – Page 61
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
Tandem Insert as shown in Figure
11-26
4 Position Insert as shown in
Figure 11-26
6 Position Insert as shown in
Figure 11-26
Figure 11-23 – Arrangement 41
Figure 11-24 – Arrangement 42
Figure 11-25 – Arrangement 43
Notes:
Notes:
Notes:
1. Accommodates mini-expanded
beam inserts
1. Accommodates mini-expanded
beam inserts
1. Accommodates mini-expanded
beam inserts
2. Shell size 2 or 3, any cavity
2. Shell size 2 or 3, “power” cavity
“C” or “F”
2. Shell size 2 or 3, “signal” cavity
“A,” “B,” “D,” or “E”
3. View shown is the mating face
3. View shown is the mating face
4. Cavity centerline at location
0.00, 0.00
4. Cavity centerline at location
0.00, 0.00
3. View shown is the mating face
4. Cavity centerline at location
0.00, 0.00
ARINC SPECIFICATION 600 – Page 62
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
Note: Drawings updated by Supplement 13
Figure 11-26 – Standard and Mini Expanded Beam Contact Layouts
ARINC SPECIFICATION 600 – Page 63
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
Note: Drawings updated by Supplement 13
Figure 11-27 – Mini and Standard Expanded Beam Plug Layouts
ARINC SPECIFICATION 600 – Page 64
ATTACHMENT 11
CONTACT POSITION IDENTIFICATION AND INSERT SIZE
Note: Drawings updated by Supplement 13
Figure 11-28 – Mini and Standard Expanded Beam Receptacle Layouts
ARINC SPECIFICATION 600 – Page 65
ATTACHMENT 12
MAXIMUM LRU THERMAL DISSIPATION
ATTACHMENT 12 MAXIMUM LRU THERMAL DISSIPATION
MAX. PERMISSIBLE
POWER DISSIPATION
(WATTS)
25
50
75
100
125
150
175
200
225
250
275
300
LRU CASE SIZE
1 MCU
2 MCU
3 MCU
4 MCU
5 MCU
6 MCU
7 MCU
8 MCU
9 MCU
10 MCU
11 MCU
12 MCU
MAX. PERMISSIBLE POWER DISSIPATION
FOR EQUIPMENT WITHOUT COOLING
OPENINGS (WATTS) 1
7
10
12
15
17
20
22
25
27
30
32
35
Note also Section 3.1.3.2, Power Dissipation, and Section 3.5.4.5, Coolant Air
Pressure Drop Through the Equipment – Level 1 and Level 2, which refer to the two
different air cooling pressure drops of which only one level should be specified for a
given LRU in an Equipment Characteristic.
1
Equipment not requiring forced air cooling is expected to pass
the thermal appraisal test set forth in Attachment 14.
ARINC SPECIFICATION 600 – Page 66
ATTACHMENT 13
ENVIRONMENTAL CONDITIONS FOR ELECTRICAL/ELECTRONIC EQUIPMENT INSTALLED IN CONTROLLED
TEMPERATURE AND PRESSURIZED LOCATIONS
ATTACHMENT 13 ENVIRONMENTAL CONDITIONS FOR ELECTRICAL/ELECTRONIC
EQUIPMENT INSTALLED IN CONTROLLED TEMPERATURE AND PRESSURIZED
LOCATIONS
CONDITION
COMPONENT
ENVIRONMENT
MCU SECTION 3.1
OF ARINC 600
RACK
SECTION 3.2
OF ARINC 600
CONNECTOR
SECTION 3.3
OF ARINC 600
WIRE
INTEGRATION
SECTION 3.4
OF ARINC 600
VIBRATION
RTCA DO-160() Section
8.0, Category “B” of
Table 8-1 and Figure 8-1
(Preferred), or *
Per Airplane
Certification
Requirements
Attachment 19
Sections 19.4.15
and 19.5.12
Per Airplane
Certification
Requirements
MECHANICAL
SHOCK
RTCA DO-160()
Section 7.0
Attachment 19
Sections 19.4.16
and 19.5.13
ACCELERATION
9G 2-Axis, 2G Upward,
4.5G Downward
Per Airplane
Certification
Requirements
Per Airplane
Certification
Requirements
Per Airplane
Certification
Requirements
Per Airplane
Certification
Requirements
HUMIDITY
RTCA DO-160()
Section 6.0, Category “A”
SALT SPRAY
ALTITUDE
LOW
TEMPERATURE
HIGH
TEMPERATURE
THERMAL
CYCLING
(SHOCK)
Attachment 19
Sections 19.4.14
and 19.5.11
Attachment 19
Sections 19.4.19
and 19.5.16
RTCA DO-160() Section
4.0, Class Y, Category A1 of Table 4-1
RTCA DO-160() Section
4.0, Class Y, Category A1 of Table 4-1
RTCA DO-160() Section
4.0, Class Y, Category A2 of Table 4-1
RTCA DO-160()
Section 5.0 Category “C”
Attachments 19
Sections 19.4.11
and 19.5.9
Notes:
1. * Category “O” of Table 8-1 and Figure 8-2 (Acceptable)
2. These are not to be construed as test requirements but are
presented as representative environmental conditions to be found in
actual service.
3. Unless otherwise noted, the latest version of RTCA DO-160 applies
4. Table updated by Supplement 5
ARINC SPECIFICATION 600 – Page 67
ATTACHMENT 14
THERMAL APPRAISAL TEST
ATTACHMENT 14 THERMAL APPRAISAL TEST
14.1 Purpose
This test is conducted on the LRU to determine:
a. The total wattage input and actual heat dissipation for all modes of electrical
operation.
b. The temperature of equipment sidewalls at the Thermal Design Condition.
c. Pressure drop through the equipment versus coolant air flow rate.
d. Temperature characteristics at the Thermal Design Condition and other
anticipated environmental operating conditions (See Table 14-1).
14.2 Apparatus
14.2.1 Test Chamber and Airplane Mounting Simulation
For the Cooling Evaluation Test, a test facility capable of producing the
environmental conditions of Table 14-1, should be employed. A suitable test
chamber and airplane mounting simulation is depicted in Figure 14-1. It is
recommended that airflow be ducted in accord with Figures 14-2a, 14-2b, and 14-2c
(as appropriate) to ensure the proper airflow distribution and ambient temperature
surrounding the LRU.
14.2.2 Instrumentation
14.2.2.1 Accuracy of the Test Apparatus
All instruments and test equipment used in conducting the test shall conform to
laboratory standards whose calibration is traceable to the appropriate national prime
standards.
14.2.2.2 Measurement Tolerances
The maximum allowable tolerances on measurements (excepting those required for
a heat balance) shall be as follows:
a. Temperature
b. Coolant Flow
c. Pressure:
Differential
Atmospheric
d. Power
e. Relative Humidity
± 2 degrees C
± 0.45 kg hr-1 or ± 3% of the test unit flow rate,
whichever is greater.
± 5%
± 1%
± 2 watts or 3% of the test unit power
dissipation, whichever is greater
± 15%
14.2.2.3 Measurements for Thermal Appraisal Test
Suitable instrumentation should be provided to measure the items below, as
applicable, during testing. (For temperature measurements “suitable
instrumentation” techniques are defined in Section 14.3.2.4) Figure 14-3 delineates
the instrumentation layout with respect to the test chamber and other apparatus.
The encircled numerals in Figure 14-3 correspond to the following measurements:
ARINC SPECIFICATION 600 – Page 68
ATTACHMENT 14
THERMAL APPRAISAL TEST
T1
T2
T3
T4
T5
T6
T7
T8
T9
T10
P1
P2
P3
M1
M2
H1
H2
Q1
Q2
F1
Ambient temperature external to the test chamber
Bulk temperature of the coolant entering the test chamber
Bulk temperature of the coolant entering the test unit (coolant inlet temperature). For
ARINC 600 cooling, locate this measurement 6 mm from the bottom surface of the test
unit and centered with respect to the coolant opening in the equipment tray. For ARINC
404A cooling, locate 6 mm above the top surface of the test unit and centered with
respect to the test unit. (Several measurements may be required where gradients exist.)
Bulk temperature of the bypass flow entering the test chamber.
Ambient temperature surrounding the equipment rack as determined by the air
temperature centered with respect to and 76 mm forward of the front face of the test unit
(excluding such projections as handles and knobs).
Bulk temperature of the bypass airflow exiting the test chamber.
Test unit’s vertical external surface temperatures; i.e., front, back, and sides.
(Measurement to be representative of the average surface temperature. Several
measurements may be required on a surface where gradients exist.)
Temperature of simulated unit surfaces facing the test unit (simulated unit working
surfaces).
Bulk temperature of the coolant exiting the test chamber.
Surface temperature of Temperature Critical Parts inside the test unit where the number
of parts instrumented should be 10 parts or 10% of the total, whichever is greater, up to a
total number of 50 parts. It is recommended that there should be at least one
measurement per printed-circuit-board. Additional part monitoring could be performed
provided the temperature monitoring does not significantly alter the data of the critical
part monitoring.
Ambient pressure external to the test chamber.
Ambient pressure external to the test unit.
Differential pressure, total to total (in mm of H20) from the test unit coolant inlet to outlet.
Determine using a separate pressure drop test setup. The pressure drop should not
include the drop across the shelf opening or other miscellaneous losses external to the
LRU.
Mass flow rate of the coolant through the test unit.
Mass flow rate of the bypass flow through the test chamber (separate from the test unit’s
coolant flow).
Relative humidity of the coolant entering the test unit (This may be calculated from
measurements made at the air source.)
Relative humidity of the bypass flow entering the test chamber. (This may be calculated
from measurements made at the air source.)
Test unit’s heat dissipation. (Equal to power input to the test unit minus power output
from the test unit not dissipated as heat.)
Simulated unit’s power input.
Test unit’s functional performance characteristics.
Notes:
*
Not required for tests of units which do not require forced air
cooling.
ARINC SPECIFICATION 600 – Page 69
ATTACHMENT 14
THERMAL APPRAISAL TEST
14.2.2.4 Temperature Measurement Techniques
Thermocouples will be the standard temperature sensors for this testing. They must
be constructed of a wire size equal to or smaller than 30 AWG.
a. Surface Temperature
The temperature sensor should be located to make good thermal contact
with the surface to be measured and yet minimize the error due to the
presence of the sensor. Where necessary, the sensor leads should be
insulated electrically from the surface, but should be held in intimate thermal
contact with the surface for at least 6 mm measured from the thermocouple
junction. Where an adhesive bond is employed; its thickness, total amount,
and distribution should be commensurate with the requirements of good
thermal contact and a minimum disturbance of the normal temperature
distribution. Figure 14-4 shows an acceptable thermocouple installation on a
test unit case.
Surface temperature measurements on electronic parts should be located, if
possible, at the point which will yield the maximum surface temperature.
Figure 14-5 and 14-6 depict satisfactory thermocouple attachment methods
for several common part types. Whenever the application of the
thermocouple may appreciably affect the temperature field on a part,
consideration should be given to using smaller gauge thermocouples and to
the method of installation.
b. Ambient Temperature
Ambient temperature thermocouples should have at least fifty diameters of
bare wire exposed in each leg of the thermocouple junction.
c. Bulk Airflow Temperature
The measurement of bulk coolant temperature and/or airflow entering or
exiting the test chamber is complicated by the fact that at any station in the
moving airstream, gradients exist. To determine a bulk temperature either
mechanical mixing must be supplied or a study of the temperature profile
must be made. When adequate mixing of the airflow is employed, one
temperature sensor in the air would be a sufficient indication of bulk
temperature. As with ambient temperature measurements, at least fifty
diameters of bare wire should be exposed to the airflow in each leg at the
thermocouple junction. At the test unit’s coolant inlet, several thermocouple
measurements may be required to establish the mean inlet temperature.
COMMENTARY
When air flows in a duct, bulk temperature must be calculated
because of the inherent thermal and velocity gradients. One method
of determination of the bulk temperature involves measuring the air
temperature at the centerline of the duct and the duct wall
temperature at the same station. The duct should be sized to yield a
Reynolds Number in the neighborhood of 10,000 when the flow rate
is in the expected range. The duct should be well insulated in order to
minimize the temperature difference between the air and the duct.
The centerline thermocouple should be located at a point of welldeveloped flow. With the preceding configuration, the following
equation will give the bulk temperature at the station where the
measurements were made:
ARINC SPECIFICATION 600 – Page 70
ATTACHMENT 14
THERMAL APPRAISAL TEST
tb = 0.81 tcl + 0.19 td
where:
tb = bulk temperature
tcl = temperature at the centerline of the duct
td = temperature of the duct wall
14.3 Test Report
The test report will contain the details and results of the Cooling Evaluation Test.
The data should include the actual test sequence used and test conditions and
results recorded as required during the test. The test record must contain a
signature and date block for certification of the test data by the test engineer.
The test data should include a complete description of all test equipment and
accessories. The test apparatus should be adequately documented by photographs,
schematics, or line drawings. All stimulus and measurement equipment should be
identified by make and model and the latest calibration date recorded.
14.4 Thermal Appraisal Test Procedure
ARINC 600 Equipment requiring forced air cooling should be tested per
Sections 14.4.1 and 14.4.2.
ARINC 600 equipment not requiring forced air cooling should be tested per
Section 14.4.3.
ARINC 404A Attachment 17 test procedure should not be used for ARINC 600
equipment to show Thermal Appraisal compliance.
Table 14-1 shows the correspondence between Environmental Operating
Conditions and test requirements for all three tests.
14.4.1 Upward Flow Forced Air Cooling
This test is to be performed using the air flow arrangement of Figure 14-2a.
Step 1
Pre-Test Performance Record
Prior to instrumentation of the test unit it must be operated and a record made of all
data necessary to determine that the test unit complies with the applicable
equipment performance standards. These data comprise the F1 measurement of
Section 14.2.2.3 and will provide the criteria for checking the validity of the test
regarding satisfactory performance of the test unit during and at the conclusion of
the test.
Step 2
Heat Dissipation
Measure total wattage input and determine the actual heat dissipation in watts for all
modes of electrical operation for which the equipment was designed; e.g., standby,
receiving, transmitting, etc. These measurements are to be made at the laboratory
ambient temperature which shall be recorded.
Identify the electrical operating mode corresponding to Maximum Steady-State Heat
Dissipation (see Paragraph 3.5.1.4).
ARINC SPECIFICATION 600 – Page 71
ATTACHMENT 14
THERMAL APPRAISAL TEST
Step 3
Instrumentation
Instrument the test unit per Figure 14-3.
Step 4
Installation
Install the test unit in the test facility.
Step 5
Normal Ground Description (Thermal Design Condition)
With the test unit operating at Maximum Steady-State Heat Dissipation, Stabilize the
equipment at the conditions representing normal ground operation as given in Table
14-1. (The test may be performed at ambient pressure conditions other than 101.3
kPa provided the density, in kg m-3, is recorded.)
Record the Section 14.2.2.3 data. Determine that the part temperature limits, test
unit sidewall temperatures, and pressure drop meet the requirements of Table 14-1.
COMMENTARY
A heat balance made using the step 5 data and other measurements
as necessary will check the performance of the test facility and
associated instrumentation. The measured total heat dissipation of
the test unit and simulated units should equate to the net heat
transferred through the test chamber walls and the heat transferred to
the airflows (coolant airflow through the test unit and bypass airflow
through the test chamber). A heat balance which equates the heat
inputs with the heat outputs within 10% shows that the test facility is
functioning properly with all significant heat paths accounted for.
Step 6
High Temperature Startup
With the test unit and simulated units turned off and no coolant flow through the test
unit, stabilize the equipment at the ambient temperature given in Table 14-1 for High
Temperature Startup.
Operate the test unit at Maximum Steady-State Heat Dissipation for 30 minutes
beginning with the “ON” cycle for equipment designed for intermittent power peaks.
Test conditions should conform to the data representing High Temperature Startup
in Table 14-1. Cooling airflow through the test unit is turned on. The simulated units
are turned on and adjusted for the same Q2 (input power) as was required in Step 5
to maintain T8 (simulated unit working surface temperature) at 60 °C. The test
chamber’s ambient temperature is held constant. Record the data of 14.2.2.3 at the
beginning and end of the test. Record measurements:
T3, T4, T5, T7, T10, M1, M2, and Q1 at 10-minute intervals throughout the 30minute test. Determine that the part temperatures remain less than the
manufacturer’s maximum allowable temperature during the 30-minute test (see
Table 14-1, Requirements).
Step 7
Severe Continuous Operation
With the test unit operating at Maximum Steady-State Heat Dissipation, stabilize the
equipment at conditions representing Severe Continuous Operation as given in
Table 14-1.
Record the data of Section 14.2.2.3.
ARINC SPECIFICATION 600 – Page 72
ATTACHMENT 14
THERMAL APPRAISAL TEST
Determine that the part temperatures are less than the manufacturer’s maximum
allowable temperature (see Table 14-1).
Step 8
Normal Flight Operations
With the test unit operating at Maximum Steady-State Heat dissipation, stabilize the
equipment at conditions representing Normal Flight Operation as given in
Table 14-1.
Record the data of Section 14.2.2.3.
Determine that part temperature limits and test unit sidewall temperatures meet the
requirements of Table 14 1.
Step 9
Emergency No-Cooling Test
Stabilize the equipment to the same conditions as in Step 8. Reduce the unit flowthrough cooling airflow to zero, while maintaining the chamber bypass airflow rate.
Increase T5 (ambient air temperature surrounding equipment rack) from 45 °C to
60 °C linearly over a 90-minute time period. Record the data of 14.2.2.3 at the
beginning and end of the test. Record measurements: T5, T8, T7, and F1 at 15
minute intervals throughout the 90-minute test.
COMMENTARY
While total loss of cooling air is remote, it is not impossible. For this
reason, flight-essential equipment (i.e., usually powered by the
battery bus) should be designed to survive the above test conditions.
The individual equipment ARINC Characteristic will state if Step 9 is
to be conducted.
Step 10
Post-Test Checkout
Return the equipment to laboratory ambient and stabilize. Operate the test unit
recording the pre-test performance data, Step 1.
Determine if the test unit complies with applicable equipment performance
standards.
Inspect the test unit recording all damage or deterioration resulting from the test.
14.4.2 Downward Flow Forced Air Cooling
This test is to be performed using the air flow arrangement of Figure 14-2b.
Conduct test per Steps 1 through 10 of Section 14.4.1.
14.4.3 Equipment not Requiring Forced Air Cooling
This test is to be performed using the air flow arrangement of Figure 14-2c. Conduct
test per Steps 1 through 10 of Section 14.4.1 with the following differences.
a. T2, T9, P3, M1, and H1 measurements are not required.
b. Duct C of figure 14-2c will remain enclosed at all times.
c. Duct B is the Bypass Air Inlet and Duct A is the Bypass Air Outlet.
ARINC SPECIFICATION 600 – Page 73
ATTACHMENT 14
THERMAL APPRAISAL TEST
Table 14-1 – Correspondence between Environmental Operating and Test Requirements for
ARINC 600 Avionic Equipment
TEST CHAMBER ENVIRONMENT
M1
ENVIRONMENTAL COOLANT
AIRFLOW
OPERATING
RATE (b)
CONDITION
kg/hr/kW
Normal Ground
Operation
High Temp. Startup
(30 min Duration)
Severe Continuous
Operation
Normal Flight
Operation
TEST UNIT REQUIREMENTS
T7
P3
PART
TEMP OF
SIMULATED TEMP
UNIT
LIMIT
WORKING
SURFACE
ºC
MAXIMUM
EQUIPMENT
SIDEWALL
TEMP
AVG/HOTSPOT
ºC
TOTAL
PRESS.
DROP
60/65
T3
T5
T8
COOLANT
TEMPERATURE
AT EQUIPMENT
INLET
ºC
AMBIENT AIR
SURROUNDING
EQUIPMENT
RACK (c)
ºC
T10
220
40
50
60
Design
201
70
70
See Note (a) Maximum
210
55
65
75
Maximum
136
30
45
60
Design
60/65
Notes, specific:
a.
Operate at the same Q2 power which was required in Step 5
to maintin T8 at 60 °C.
b.
The maximum allowable relative humidity is 40%.
c.
Air velocities immediately surrounding the test unit should not
be greater than those caused by air movement due to natural
convection effects.
Notes, general:
d.
Test unit shall be operating at Maximum Steady State Heat
Dissipation.
e.
Equipment thermal status shall be steady-state except during
High Temperature Startup.
f.
The test unit shall demonstrate acceptable functional
performance in all Environmental Operating Conditions.
g.
For download Airflow tests, T3 is measured but is not a test
control parameter, T5 is the temperature controlling
parameter and should be set to the values showin the T3
Column. Values shown under T5 should be disregarded.
h.
Disregard M1, T3, and P3 for Section 14.4.3 tests (units not
requiring forced Air Cooling).
i.
See Section 14.2.2.3 and Figure 14-3 for definition and
location of instrumentation.
MM H2O
See
3.5.4.5
ARINC SPECIFICATION 600 – Page 74
ATTACHMENT 14
THERMAL APPRAISAL TEST
Figure 14-1 – Standard Test Chamber
(See flag notes for mechanical detail)
Figure 14-1 Flag Notes
1. Test Chamber
The test chamber’s internal dimensions should enclose a space approximately 0.9 m square
by 0.5 m high. An ARINC 404A test chamber modified to the configuration shown in
Figure 14-1 can be used. The test chamber (and associated inlet and exit ducting) should be
air tight and thermally insulated to the extent necessary.
Ambient temperature surrounding the equipment rack T5, see Figure 14-3, is the standard for
test chamber control. The means for maintaining this temperature constant should be
additional airflow (bypass flow) through the test chamber other than that required for dedicated
coolant flow through the test unit. Flow control provisions should be capable of maintaining the
T5 temperatures constant within ±2 °C of any selected test temperature. To ensure that
ambient velocities surrounding the test unit remain comparable to those which would occur
from natural convection effects; bypass flowrate M2 should be limited to 80 kg of air per hour
maximum, and the temperature differential between T4 and the T5 ambient temperature
should be limited to ± 5 °C. Airflow through the test chamber and through the test unit should
be produced by positive pressure at ducts B and C for upward airflow cooling and produced by
negative pressure at ducts B and C for downward airflow cooling. For units not requiring
forced air cooling, duct B is the bypass air outlet. The inlet and outlet ducts should not be
coupled into a closed-loop system.
2. Air Inlet and Exhaust Ducts
Airflow ducts should be provided in the locations shown. Their functions in ARINC 600 cooling
evaluation tests are shown schematically in Figure 14-2.
ARINC SPECIFICATION 600 – Page 75
ATTACHMENT 14
THERMAL APPRAISAL TEST
3.
4.
5.
6.
Duct A
Functions either as an exhaust duct for upward airflow tests or an inlet to the test chamber for
downward airflow tests.
Duct B
Functions as a bypass airflow control duct. It is an inlet for upward airflow tests and for tests
not requiring forced air cooling. It is an exhaust for downward airflow tests.
Duct C
Should be coupled to the plenum as shown in Figure 14-1 or to the equipment shelf coolingaperture when the plenum shelf is simulated by a solid piece of material. It should be thermally
insulated from the test chamber ambient air and the duct B entrance airflow. In Section 14.4.1
tests it should function as an inlet duct to provide the M1 upward airflow required through the
test unit. For Section 14.4.2 tests it should function as an exhaust duct for the M1 downward
airflow through the test unit. For Section 14.4.3 tests it should be closed.
Plenum Shelf
The plenum shelf (equipment shelf) is used to support the equipment and simulated units and
to act as a baffle to deflect the airflow entering the test chamber through duct B. It represents
the plenum shelf in the airplane, but does not have to be an actual plenum in the test setup. It
should be 320 to 500 mm deep and 635 ± 25 mm long, including insulation if required.
Thickness is optional. There should be no holes that might allow passage of air through the
plenum shelf except as required to couple the cooling aperture (see Attachment 9) with
duct C. The plenum shelf is not intended to act as heat a sink in ARINC 600 cooling. Where an
actual plenum (as depicted in Figure 14-1) is employed, it should be thermally insulated from
the test chamber ambient and the duct B entrance airflow. An alternate approach is to use a
solid shelf fabricated of some low-conductivity non-metallic material (such as a fiberglass
laminate or wood) and to couple duct C to the equipment shelf cooling-aperture.
Simulated Unit.
(Two required, one each side of the test unit.) The simulated unit shall be 320 ±5 mm deep by
194 ±2 mm high. The plane of the simulated unit facing the test unit (working surface) should
be parallel to and 8.9 ± mm from the test unit sidewall. The simulated unit back-vertical edge
should be aligned with the back edge of the unit under test. Temperature of the working
.
surface T8 is the standard for simulated unit control. It is recommended that the working
.
surface be fabricated of aluminum or copper plate and heated by electrical resistance heaters
evenly distributed over the plate side opposite the working surface to achieve a uniform
temperature distribution. The working surface should be smooth and solid (no holes that might
allow the passage of air through the plane). The minimum emissivity of the working surface
should be 0.85. The working surface should be thermally insulated from the plenum shelf to
preclude the existence of a conduction path from the working surface to the test unit. The side
opposite the working surface should be insulated to minimize heat transfer to the test chamber
ambient. Balsa is a satisfactory thermal insulation for the plate side opposite the working
surface (the plate edges do not need to be insulated except from the plenum shelf).
Simulated Shelf
A solid shelf 320 to 500 mm deep by 635 ±25 mm long. Thickness is optional. The shelf shall
be mounted 12.7 ±1.3 mm above the simulated units and aligned to cover the full length and
width of both simulated units when viewed from above. The shelf should be fabricated from
some low-conductivity non-metallic material, such as a fiberglass laminate or balsa wood.
LRU Support
ARINC SPECIFICATION 600 – Page 76
ATTACHMENT 14
THERMAL APPRAISAL TEST
An equipment mounting surface with guide rails and cooling air aperture should be used which
is representative of the airplane installation. It will provide flow control openings, a backplate
for electrical connector mounting, and usually the mounting surface for the hold down
mechanism. The installation must be aligned so that the back vertical surface of the test unit
(excluding projections) is flush with the back vertical surfaces of the simulated units. The
equipment mounting surface may be installed as part of the top surface of an air plenum as
shown in Figure 14-1. Alternatively, the coolant airflow may be ducted directly from duct C to
the cooling aperture but, in either case, the airflow path must be thermally shielded from the
duct B entrance airflow.
Figure 14-2a – Airflow Schematic, ARINC 600 Cooling (Upward Airflow)
ARINC SPECIFICATION 600 – Page 77
ATTACHMENT 14
THERMAL APPRAISAL TEST
Figure 14-2b – Airflow Schematic (Downward Airflow)
Figure 14-2c – Airflow Schematic (Units Not Requiring Forced Air Cooling)
ARINC SPECIFICATION 600 – Page 78
ATTACHMENT 14
THERMAL APPRAISAL TEST
Numbers coincide with Paragraph 14.2.2.3
Letters F = Functional
*
Q = Power Dissipation
H = Specific Humidity
T = Temperature
M = Mass Flowrate
∆ = Differential
Section 14.4.2 Thermal Appraisal Tests Only (Downward
Airflow)
Figure 14-3 – Instrumentation Schematic, Test Chamber
ARINC SPECIFICATION 600 – Page 79
ATTACHMENT 14
THERMAL APPRAISAL TEST
Figure 14-4 – Thermocouple Installation on a Test Unit Case
(30 AWG Wire Recommended)
ARINC SPECIFICATION 600 – Page 80
ATTACHMENT 14
THERMAL APPRAISAL TEST
Figure 14-5 – Thermocouple Installation on a Resistor or Diode
(36 to 30 AWG Wire Recommended Dependent upon Size of Part)
ARINC SPECIFICATION 600 – Page 81
ATTACHMENT 14
THERMAL APPRAISAL TEST
Figure 14-6 – Thermocouple Installation on a Transistor Package
(36 to 30 AWG Wire Recommended Dependent upon Size of Part)
ARINC SPECIFICATION 600 – Page 82
ATTACHMENT 15
LRU MOUNTING PATTERN – SIZE 1 CONNECTOR
ATTACHMENT 15 LRU MOUNTING PATTERN – SIZE 1 CONNECTOR
Connector Receptacle Mounting Pattern for 1 MCU Only:
Attachment 15 Notes:
1. Positional tolerance (TOL) is dependent upon the clearance hole size
limits chosen, as well as the outer boundary of the connector
mounting threads position tolerance.
ARINC SPECIFICATION 600 – Page 83
ATTACHMENT 15
LRU MOUNTING PATTERN – SIZE 1 CONNECTOR
Connector Receptacle Mounting Pattern for 2 through 12 MCU:
Attachment 15 Notes (continued):
2. Datum feature P is the external surface for the rear flange mounting
method of connector installation.
3. Datum feature P is the internal surface for the front flange mounting
method of connector installation. The 5.21 mm (0.205 inch) minimum
notch depth applies only in this case.
4. Refer to Attachment 2 for front and rear flange connector mounting
illustrations.
ARINC SPECIFICATION 600 – Page 84
ATTACHMENT 15
LRU MOUNTING PATTERN – SIZE 1 CONNECTOR
Connector Receptacle Mounting Pattern for 2 through 12 MCU:
Attachment 15 Notes (continued):
5. The presence or utilization of these four mounting holes is optional.
ARINC SPECIFICATION 600 – Page 85
ATTACHMENT 15
LRU MOUNTING PATTERN – SIZE 1 CONNECTOR
Connector Receptacle Mounting Pattern for 3 through 12.
Attachment 15 Notes (continued):
6. The presence or utilization of these eight mounting holes is optional.
7. Attachment 15 drawing updated by Supplements 12 and 13.
ARINC SPECIFICATION 600 – Page 86
ATTACHMENT 16
SHELF/RACK CUTOUT – SIZE 1 CONNECTOR
ATTACHMENT 16 SHELF/RACK CUTOUT – SIZE 1 CONNECTOR
Connector Plug Mounting Pattern for 1 through 12 MCU:
Attachment 16 Notes:
1. Datum feature E is the rearmost surface for externally mounting the
connector plug shell. The 6.35 mm (0.250 inch) maximum notch end
applies only in this case.
2. Datum feature E is the interior surface for internally mounting the
connector plug shell. The 5.21 mm (0.205 inch) minimum notch depth
applies only in this case.
ARINC SPECIFICATION 600 – Page 87
ATTACHMENT 16
SHELF/RACK CUTOUT – SIZE 1 CONNECTOR
Connector Plug Mounting Pattern for 2 through 12 MCU:
Attachment 16 Notes (continued):
3. The presence or utilization of these four mounting holes is optional.
ARINC SPECIFICATION 600 – Page 88
ATTACHMENT 16
SHELF/RACK CUTOUT – SIZE 1 CONNECTOR
Connector Plug Mounting Pattern for 3 through 12 MCU:
Attachment 16 Notes (continued):
4. The presence or utilization of these four mounting holes is optional.
5. Attachment 16 drawings updated by Supplement 13.
ARINC SPECIFICATION 600 – Page 89
ATTACHMENT 17
CONNECTOR ENGAGING SEQUENCE
ATTACHMENT 17 CONNECTOR ENGAGING SEQUENCE
Note: Fully mated dimensions corrected by Supplement 19.
ARINC SPECIFICATION 600 – Page 90
ATTACHMENT 18
INDEX PIN CODING
ATTACHMENT 18 INDEX PIN CODING
Notes:
1. Darkened portion indicates extended part of post in plug. Light
portion indicates key hole in receptacle.
2. Mating faces shown with TOP up.
3. It is possible to insert a Size 1 plug into a Size 2 receptacle when
connector is center-mounted on like size box/rack. Therefore, it is
necessary to assign Index pin codes exclusively to same size boxes
with Size 1 or Size 2 connectors.
ARINC SPECIFICATION 600 – Page 91
ATTACHMENT 18
INDEX PIN CODING
The following table defines the Index Pin coding for positions 1-216.
Pins 100-216 were added in Supplement 13.
ARINC SPECIFICATION 600 – Page 92
ATTACHMENT 18
INDEX PIN CODING
ARINC SPECIFICATION 600 – Page 93
ATTACHMENT 18
INDEX PIN CODING
ARINC SPECIFICATION 600 – Page 94
ATTACHMENT 18
INDEX PIN CODING
ARINC SPECIFICATION 600 – Page 95
ATTACHMENT 18
INDEX PIN CODING
ARINC SPECIFICATION 600 – Page 96
ATTACHMENT 19
CONNECTOR SPECIFICATION
ATTACHMENT 19 CONNECTOR SPECIFICATION
19.1 Scope
This specification covers the requirements, quality assurance criteria and test
procedures for the design and fabrication of a non- and semi-environment resisting
low insertion force rectangular connector.
19.1.1 Intended Use
The low insertion force rectangular connector is intended for use in a controlled
environment similar to that of the electrical/electronic bay area of a commercial
subsonic jet airplane. The connector shall provide the electrical interface between
the ARINC standard equipment and the airplane equipment rack.
19.1.2 Classification
Connectors covered by this specification shall be defined by the following type and
classes.
19.1.2.1 Type
The connector type defined by this Specification Control Drawing shall have a
contact engagement and disengagement system activated during the mating and
unmating process, and fully contained within the connector envelope.
19.1.2.2 Class
Given the temperature range of -65 °C (-85 °F) to +125 °C (+275 °F), the
connector class shall be defined as follows:
Class A – Unsealed Connectors
Class B – Semi-environment resisting connectors
19.2 Applicable Documents
MIL-C-81659
MIL-STD-1344
MIL-W-22759
MIL-W-81381
MIL-C-5809
MIL-I-17214
MIL-G-45204
MIL-C-17E
QQ-N-290
MIL-L-23699
MIL-H-5606
TT-I-735
TT-I-291
P-D-680
Connectors, Electrical, Rectangular, Environment Resistant, Crimp
Contacts, General Specification for
Test Methods for Electrical Connectors
Wire, Electric, Fluoropolymer-Insulated, Copper or Copper Alloy
Wire, Electric, Fluoropolymer-Insulated, Copper or Copper Alloy
Circuit Breakers, Trip-Free, Aircraft, General Specification for
Indicator, Permeability; Low MV (Go-No-Go)
Gold Plating, Electrodeposited
Cables, Radio Frequency, Flexible and Semirigid, General
Specification for
Nickel Plating (Electrodeposited)
Lubricating Oil, Aircraft Turbine Engine, Synthetic Base
Hydraulic Fluid, Petroleum Base; Aircraft, Missile, and Ordnance
Isopropyl Alcohol
Thinner, Paint, Mineral Spirits, Regular and Odorless
Dry Cleaning Solvent
ARINC SPECIFICATION 600 – Page 97
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.3 Requirements
19.3.1 Specification Sheets
The individual item requirements should be as specified herein and in accordance
with the applicable specification drawing. In the event of any conflict between the
requirements of this specification and the drawings, the latter shall govern.
19.3.2 General Requirements
In case of conflicts with this Specification and other documents, the requirements of
this Specification shall control. The items furnished under this Specification should
be capable of passing the performance verification test specified herein.
19.3.2.1 Mateability
Enough dimensional information concerning the connector design is provided herein
to ensure that other designs will be intermateable with the selected design and each
other. In addition, all crimp contacts should be intermateable and interchangeable.
Solderless wrap terminated contacts must be intermateable with crimp contacts but
need not be interchangeable.
19.3.2.2 Basic Design and Materials
The design and materials should be compatible with environmental conditions
similar to those encountered in the equipment bay areas located in the pressurized
area of a commercial subsonic jet airplane, i.e., pressure-altitude, temperature,
humidity, vibration.
19.3.2.3 Dissimilar Metals
Unless otherwise protected against electrolytic corrosion, dissimilar metals should
not be employed in intimate contact with each other in a connector or in any mated
pairs of connectors conforming to this drawing. Metals are listed according to EMF
values in Figure 19.3.2. Generally, the greater the separation of metals in the list,
the greater will be the galvanic action if bonded together and subject to moisture.
The metals toward the top of the list are less susceptible to galvanic corrosion than
those toward the bottom of the list. For maximum compatibility, materials in the
shaded areas should not have a greater potential difference than ± 0.25 volt.
19.3.2.4 Nonmagnetic Materials
All components, with the exception of screws, washers, polarizing posts and keys,
and mounting hardware should be made from materials which are classified as
nonmagnetic and the permeability of the basic connector assembly should be less
than 2.0 MU. The permeability should be checked by the instrument described in
MIL-I-17214 or equivalent.
19.3.2.5 Finish
All Metal parts should be made of corrosion-resistant materials or be protected to
meet the performance requirements of this Specification. If the shell and backshell
hardware are made of metallic materials, they should be electrically conductive.
19.3.2.6 Shell
Shell material should be of high-grade materials which provide dimensional stability
compatible with connector mateability. The shells should be capable of withstanding
horizontal, vertical and sideloads of 400 pounds, and a connector mating impact
ARINC SPECIFICATION 600 – Page 98
ATTACHMENT 19
CONNECTOR SPECIFICATION
force of 1000 pounds, based on a 40-pound equipment box with an insertion
velocity of 2 feet/second and a stopping distance of 0.03 inches.
19.3.2.7 Insert Material
Rigid insert materials should have properties which conform to the electrical and
mechanical requirements of this specification.
Figure 19.3.2 – EMF Values for Metals
ARINC SPECIFICATION 600 – Page 99
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.3.2.8 Resilient Materials
Resilient materials should have a Shore hardness, electrical and mechanical
characteristics suitable for the purpose intended.
19.3.2.9 Weight
The connector with backshell hardware and contacts should be a minimum weight
consistent with performance requirements and within the limitations of sound design
practices.
19.3.2.10
Durability
The connector should be designed and constructed to withstand handling and
maintenance functions incident to installation and service.
19.3.2.11
Seals
Class B connectors should be designed to increase the effective electrical creepage
path and prevent the ingress of moisture and contaminants. The wire sealing
member should provide suitable sealing for the range of wire diameters listed in
Table 19.3.2.11 and should not be removable from the shell.
19.3.2.12
Contacts
19.3.2.12.1
Contacts Designation
Contacts should be designated for crimp termination, or with rectangular or square
posts compatible with automatic or semi-automatic termination processes.
19.3.2.12.2
Contact Mating
Contact mating action should be designed to provide a wiped and, where possible,
back-wiped surface contact.
19.3.2.12.3
Contact Plating
Contact plating(s) should be provided on all mating surfaces with a thickness
compatible with accepted design practices for high reliability connectors. Particular
attention is required at the contact-to-wire interface (crimp) and contact-to-contact
surface. All other surfaces should be adequately treated for corrosion and moisture
resistance.
19.3.2.13
Contact Insertion/Removal
Connectors should permit individual insertion and removal of the contacts without
removing the insert of sealing members. Insertion of the contacts into and removal
of the contacts from the insert should be accomplished with the aid of standard and
qualified tools.
19.3.2.14
Contact Engagement
The connector should be designed such that rear access for electrical/electronic
rack applications is not required to engage contacts. The use of tools should not be
required for contact engagement.
19.3.2.15
Inserts
The inserts should be so designed and constructed with proper sections and radii
that they will not readily chip, crack, or break in assembly or normal service. Hollowtype inserts should not be used. The inserts should be so designed, constructed,
ARINC SPECIFICATION 600 – Page 100
ATTACHMENT 19
CONNECTOR SPECIFICATION
and assembled as to eliminate all air paths between contacts. The insert sealing
members (where used) should be of resilient material.
The inserts should be designed for positive locking of the contacts in the inserts.
Table 19.3.2.11 – Wire Insulation Range
Contact Size
Low Insertion Force
Signal Contact (#22)
#20
#16
#12
#8
Contact Size
Low Insertion Force
Signal Contact (#22)
#20
#16
#12
#8
19.3.2.16
Range of Outside Diameter of
Finished Wire (inches)
0.026 to 0.054
(2 seal ranges permissible)
0.040 to 0.071
0.068 to 0.103
0.097 to 0.135
0.183 to 1.255
Wire Gauge Range Contact
Required to Crimp
AWG 22,24, 26, 28
(2 crimp barrel sizes allowed)
AWG 20, 22
AWG 16, 18, 20
AWG 12, 14
AWG 8, 10
Accessories
Backshell hardware should be available to protect the mated connector from the
ingress of contaminants (water, sand, chemicals) and provide wire bundle stress
relief. Sealing-plugs should be available for unused contact cavities for class B
connectors.
19.3.2.17
Tools
Standard tools should be used for contact crimp, insertion and removal. Unique
tools should not be required by any different connector manufacturers.
19.3.3 Form Factor Requirements
A minimum number of shell sizes and contact capacities as shown in the individual
specification drawings and as discussed below should be provided:



Shell size 1 should accommodate a 1 MCU-wide LRU with 120 low insertion
force contacts on 0.100 inch center-to-center spacing, and provisions for
power and coaxial contacts (conventional type).
Shell size 2 should accommodate a 2 MCU-wide LRU, with 300 low insertion
force contacts on 0.100 inch center-to-center spacing, physical barriers for
circuit separation, and provisions for power and coaxial contacts
(conventional type).
Shell size 3 should accommodate a 3 MCU-wide LRU, with 600 low insertion
force contacts on 0.100 inch center-to-center spacing, physical barriers for
circuit separation, and provisions for power and coaxial contacts
(conventional type).
ARINC SPECIFICATION 600 – Page 101
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.3.4 Electrical Requirements
19.3.4.1 Contacts
Provisions should be provided to handle the following combinations of contacts as
shown in the individual specification drawings.
a. Low insertion force signal contacts with a 5 ampere, 115 volt, 400 Hz
continuous duty and a 7.5 ampere, 115 volt, 400 Hz intermittent duty rating.
b. Conventional power contacts to include sizes 8, 12, 16, and 20.
c. Conventional coaxial contacts as required in MIL-C-81659.
d. Fiber Optic contacts (to be determined)
19.3.4.2 Pin and Socket Power Contacts
Contacts should have the nominal electrical characteristics shown in Table 19.3.4.2.
Table 19.3.4.2 – Nominal Current Rating
Contact Size
20
16
12
8
Amperes
7.5
13.0
23.0
46.0
19.3.4.3 Coaxial Contacts
Coaxial contacts should conform to the specification drawings contained herein,
specifically Figures 19-60.1 and 19-60.2.
19.3.5 Mechanical Requirements
19.3.5.1 Forces
The force to fully engage and disengage the mated pair shells and contacts should
not exceed 27 pounds for size 1, 60 pounds for size 2, and 105 pounds for size 3.
Note: See Section 3.3.2.4.1 for maximum forces which should be
maintained on all new connector designs.
19.3.5.2 Inserts
19.3.5.2.1 Insert Interchangeability
Shell size 1 connector inserts should be interchangeable with each other, but not
with shell size 2 and 3 inserts. Shell size 2 and 3 connector inserts should be
interchangeable.
19.3.5.2.2 Insert Retention
Individual inserts should be positively retained within the connector shell, preferably
by mechanical means.
19.3.5.2.3 Contact Retention
Crimp contacts should be rear release and positively retained by the insert. The
retention mechanism should be contained in the insert. The contact should be free
of devices which can be damaged during handling and usage.
ARINC SPECIFICATION 600 – Page 102
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.3.5.3 Contacts
19.3.5.3.1 Contact Spacing
Contacts should be located on a 0.025 inch square grid pattern. For signal contacts,
the center-to-center spacing should not be less than 0.100 inches.
19.3.5.3.2 Contact Location
The connector signal contact inserts should be so designed that protected pins
should be associated with the rack mounted plug, and exposed sockets with the box
mounted receptacle.

The ARINC 727 Microwave Landing System (MLS) LRU receptacle should
use sockets for size 22 signal contacts. Larger contacts (size 20, 16, and 12)
and coaxial contacts should be pins. The rack-mounted plug should contain
the complement, that is, size 22 signal contacts should be pins while larger
contact and coaxial contact should be sockets.
19.3.5.4 Contact Actuator Mechanism (where applicable)



The actuator should be self-aligning prior to low insertion force contact
engagement with the mating connector.
The connector should be so designed that the contact actuator should be
associated with the box mounted receptacle.
The contact actuation mechanism should be so designed that no mechanical
failure will prevent unmating of the connector mated pair.
19.3.5.5 Shell (see Section 19.3.2.6)





The connector receptacle should provide surface for the bottoming of the
plug shell to ensure full connector mating.
When the plug and receptacle are fully mated, the space between the
adjacent flanges should be a minimum of 0.49 inches as shown in
Figure 19.3.5.5.
Shell designs should provide for physical barriers for circuit separation.
Minimum contact exposure should be maintained, but under no
circumstances should the contacts extend beyond the shell.
Optional alignment ribs may be provided on the connector plug. The number
of ribs and the spacing of the ribs are also optional. The connector
receptacle should not have ribs.
ARINC SPECIFICATION 600 – Page 103
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19.3.5.5 – Fully Mated Connector Definition
19.3.5.6 Shell Polarization


Shell polarization of the connector should be accomplished by means of
integral keys and keyways. Polarization should occur before contacts are in
a mated condition (low insertion force signal), and before pins begin to enter
sockets of power contacts or coaxial contacts begin engagement.
The connector shells should have a minimum of 99 polarizing positions and
should use the code defined by MIL-C-91659. Each position should be
selectable without disassembly of the connector half.
19.3.5.7 Connector Mating Sequence
The connector mating sequence should be as follows:
Shells – Polarizing Keys – Contacts
19.4 Performance Requirements
19.4.1 Performance
Connectors and contacts should be designed to meet the performance requirements
specified herein when tested in accordance with the specified methods in
Section 19.5.
19.4.2 Workmanship
The connector should be fabricated in a manner such that the criteria for
appearance, fit, and adherence to specified tolerances are observed. Particular
attention should be given to neatness and thoroughness of marking parts, plating,
welding, soldering, riveting, staking, bonding, and freedom of parts from burrs and
sharp edges.
19.4.3 Test Conditions
Unless otherwise specified, test and examinations required by this specification
should be conducted within the range of environmental conditions noted.
Temperature
20 to 30 °C (68 to 86 °F)
Relative Humidity
30 to 80 percent
ARINC SPECIFICATION 600 – Page 104
ATTACHMENT 19
CONNECTOR SPECIFICATION
Barometric Pressure
24 to 31 inches of mercury
19.4.4 Preparation of Test Sample
19.4.4.1 Signal Contacts
Half of the connector inserts in each group should be fully loaded with 22 AWG tinplated wire conforming to MIL-W-W-22759/34, and half with 24 AWG silver-plated
wire conforming to MIL-W-22759/35.
Exceptions: In one connector of each shell size, in a group which undergoes thermal
cycling, one insert in each connector should be fully loaded with 24 AWG nickelplated wire conforming to MIL-W-22759/12C or MIL-W-81381/12B and one insert in
the shell size 3 connector should be fully loaded with 22 AWG nickel-plated wire
conforming to MIL-W-22759/12C or MIL-81381/12B.
19.4.4.2 Power Contacts
Power contact inserts should be fully loaded with the appropriate wire sizes
conforming to MIL-W-22759/34. The power insert configuration should include AWG
20, 16, and 12 wires as a minimum. Different power insert combinations and
connectors may be used to include these wire sizes. The coaxial contacts should be
loaded with the appropriate coaxial cable and sizes conforming to MIL-C-17E.
19.4.4.3 Test Groups
Table 19.4.4.3 – Test Groups
Group
A
B
C
D
Connector Samples
2 mating pairs
2 mating pairs
2 mating pairs
3 mating pairs
19.4.5 Mating and Unmating Force (see Section 19.5.2)
The maximum amount of direct thrust force to engage or disengage the
mating connector halves should not exceed:



27 pounds for Size 1
60 pounds for Size 2
105 pounds for Size 3
19.4.6 Insulation Resistance (Ambient Temperature)
When tested as specified in Section 19.5.3, the insulation resistance between any
pair of contacts and between any contact and shell should be greater than 5000
megohms.
19.4.7 Insulation Resistance (Elevated Temperature)
When tested as specified in Section 19.5.4, the insulation resistance between any
pair of contacts and between any contact and shell should be greater than 1000
megohms.
ARINC SPECIFICATION 600 – Page 105
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.4.8 Dielectric Withstanding Voltage (DWV)
When tested as specified in Sections 19.5.5 and 19.5.6, the connectors should be
capable of withstanding the applicable voltage shown in Table 19.4.8 without
flashover. The maximum leakage current should be 1 miliampere.
Table 19.4.8 – Dielectric Test Voltages
Altitude
Sea Level
50,000 ft.
AC Voltage, 60 Hz (Vrms)
Dielectric Test Level
Unmated
Mated
1500
1500
500
500
19.4.9 Contact Resistance
When tested as specified in Section 19.5.7 mated low insertion force contacts
should meet the resistance requirements of Table 19.4.9.
Table 19.4.9 – Contact Millivolt Drop
19.4.10
Wire
Size
(AWG)
Test
Current
(amps)
12
16
20
22
24
26
28
23
13
7.5
5
3
2
1.5
Millivolt Drop
Maximum
After
All
Corrosion,
Others
Temp.
Durability or
Current
Cycling
60
45
65
50
65
55
55
40
45
30
40
25
35
20
Low Level Circuit
When tested as specified in Section 19.5.8, mated signal contacts should meet the
resistance requirements of Table 19.4.9.
19.4.11
Thermal Cycling
When tested as specified in Section 19.5.9, there should be no damage detrimental
to the operation of the connector. Any evidence of damage resulting from this test
should be a cause for rejection.
19.4.12
Maintenance Aging
When tested as specified in Section 19.5.10, connectors should be capable of
meeting the performance requirements of Section 19.4.13 and the remaining test
sequence in Table 19.5.1. Failure to complete these tests should be cause for
rejection.
ARINC SPECIFICATION 600 – Page 106
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.4.13
Contact Insertion and Removal Force
When tested as specified in Section 19.5.10, the individual contact insertion and
removal forces should not exceed the values in Table 19.4.13.
Table 19.4.13 – Insertion/Removal Forces
Contact Size
Signal Contacts
22
20
16
12
8
Coaxial Contacts
Fiber Optic Contacts
19.4.14
Axial Loads (lbs.)
Insertion
Removal
10
8
15
10
20
15
25
20
30
25
30
25
15
10
Moisture Resistance (Humidity)
When tested as specified in Section 19.5.11, the unmated connector halves should
have an insulation resistance greater than 1 megohm 1-2 hours after humidity, and
greater than 5000 megohms after 24 hours of conditioning at room ambient.
19.4.15
Vibration
When tested as specified in Section 19.5.12, a current discontinuity of 1
microsecond or greater, or evidence of cracking, breaking, or loosening of parts
should be cause for rejection.
19.4.16
Physical Shock
When tested as specified in Section 19.5.13, a current discontinuity of 1
microsecond or greater, or evidence of cracking, breaking, or loosening of parts
should be cause for rejection.
19.4.17
Durability
When tested as specified in Section 19.5.14, connectors should show no damage
detrimental to the operation of the connector, and should meet the contact
resistance requirements of Section 19.4.9. Failure to complete this test because of
mechanical malfunction of the connector should be cause for rejection.
19.4.18
Temperature Life
When tested as specified in Section 19.5.15, the connector should meet the
performance requirements of the remaining test sequence shown in Table 19.5.1.
19.4.19
Salt Spray (Corrosion)
When tested as specified in Section 19.5.16, unmated connectors and contacts
should show no exposure of basic metal due to corrosion which will adversely affect
the electrical and/or mechanical integrity.
19.4.20
Insert Retention
When tested as specified in Section 19.5.17, the connector insert assembly should
retain its normal position in the connector shell for the specified load and should
show no physical damage.
ARINC SPECIFICATION 600 – Page 107
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.4.21
Contact Retention
When tested as specified in Section 19.5.18, the signal contacts in wired unmated
connectors should withstand an axial load as specified in Table 19.4.21. Power and
coax contacts should withstand an axial load as specified in Table 19.4.21. The
axial displacement of the contacts should not exceed 0.015 inch, and there should
be no dislodging or damage to the contact, connector insert, or the contact retention
mechanism.
Table 19.4.21 – Contact Retention
Contact Size
Signal Contacts
20
16
12
8
Coaxial Contacts
Fiber Optic Contacts
19.4.22
Axial Load (Min), lbs.
12
20
25
30
35
35
20
Seal Leakage
When tested in accordance with Sections 19.5.19 and 19.5.3, mated connectors
should have a minimum insulation resistance of 100 megohms. In addition, the
mated connectors should withstand a dielectric test voltage of 1500 Vrms,
60 Hz, with a maximum leakage current of 1 milliampere when tested according to
Section 19.5.5.
19.4.23
Flexure Bend
When tested in accordance with Section 19.5.20, contacts should show no evidence
of stress cracks either on the plating or on the basic metal. Any cracks evident from
this test when viewed at 10X magnification should constitute a contact failure.
19.4.24
Contact Walk-Out
When tested as specified in Section 19.5.21, contacts should not become dislodged
from their normal position.
19.4.25
Contact Current Switching
When tested as specified in Section 19.5.22, there should be no contact annealing
(check spring-back), sticking, welding, or melting away. In addition, the millivolt drop
should not exceed 150% of the initial millivolt drop values after the contacts have
been engaged one time post test.
19.4.26
Contact/Circuit Breaker Compatibility
When tested as specified in Section 19.5.23, there should be no contact annealing,
sticking, welding, or other damage detrimental to the operation of the contact
system. In addition, the millivolt drop should not exceed 150% of the initial millivolt
drop values after the contacts have been engaged one time post test.
19.4.27
Fluid Immersion
a. Seals – After immersion in the fluids as specified in Table 19.5.24,
connectors should unmate and mate properly and resilient materials should
not swell to the extent that cracks and tears appear. There should be no
ARINC SPECIFICATION 600 – Page 108
ATTACHMENT 19
CONNECTOR SPECIFICATION
evidence of material reversion. Shells, plating and dielectric materials should
show no evidence3 of deterioration, distortion or material reversion.
b. Retention System – After immersion in the fluids as specified in Table
19.5.24, contact retention should meet the requirements of Section 19.4.21
when tested in accordance to Section 19.5.18. The insert retention capability
should meet the requirements of Section 19.4.20 when tested as specified in
Section 19.5.17. Effects of the fluids on resilient sealing members should not
be a consideration of this test.
19.4.28
Contact Crimp Tensile Strength
When tested in accordance with Section 19.5.25, the minimum tensile load required
to separate the wire from the contact either by pulling out of the crimp barrel or
breaking of the wire should not be less than the applicable limit in Table 19.4.28.
Table 19.4.28 – Tensile Strength
Wire
Size
Silver or Tin-Plated
Cu
28
26
24
22
20
18
16
14
12
10
8
3
5
8
12
20
40
50
70
110
150
220
High Str.
Cu
6
8
15
---------
Nickel-Plated
Cu
2
4
6
8
15
25
29
60
100
135
200
High Str.
Cu
5
6
12
---------
* H.S. Cu is High Strength Copper
19.4.29
Axial Concentricity
When tested in accordance with Section 19.5.26, Total Indicator Reading (TIR)
should not exceed 0.030 for size 8, 0.012 for sizes 12 through 16, and 0.011 for
sizes 20 through 28. Only contacts which are end positioned in the crimping tool are
required to be checked for axial concentricity at the mating end after crimping to
wire.
19.4.30
Contact Probe Damage
When tested in accordance with Section 19.5.27, contacts should withstand the
bending moment without evidence of physical damage, and should pass the Low
Level Resistance requirements when tested in accordance with paragraph 19.5.8.
19.4.31
Voltage Standing Wave Ratio (VSWR)
When tested in accordance with Section 19.5.28, the VSWR should not exceed
1.70:1 for size 1 and 1.30:1 for size 5 coaxial contacts.
ARINC SPECIFICATION 600 – Page 109
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.4.32
Insertion Loss
The insertion loss should not be more than 0.3 dB greater than the loss in the
reference cable described in Section 19.5.29. The measurement procedure should
be in accordance with Section 19.5.29.
19.5 Performance Verification Test Procedures
19.5.1 Verification Tests
Test specimens described in Section 19.4.4 should be subjected to the test
sequence shown in Table 19.5.1.
19.5.2 Mating and Unmating Force (see Section 19.4.5)
The connectors should be tested in accordance with Method 2013 of MIL-STD-1344
with the following addition:
1. Prior to measuring forces, the connectors (including all contacts) should be
mated and unmated 3 times. During the third cycle of mating and
subsequent unmating, the force involved should be measured.
19.5.3 Insulation Resistance (Ambient Temperature) (See Section 19.4.6)
Unmated connectors should be tested as specified in Method 3003.1 of
MIL-STD-1344. The following details and exceptions should apply:
1. A minimum of 20 signal contacts in each insert should be tested. The
location of the contacts should be selected such that measurements are
distributed to include the corners, sides, and center of the insert.
2. 100% of the power and coaxial contacts should be tested.
3. The tolerance of the applied voltage should be ±10%.
4. Measurements should be made between adjacent pairs of contacts and
between the shell and contacts adjacent to the shell.
19.5.4 Insulation Resistance (Elevated Temperature) (See 19.4.7)
Unmated connectors should be tested as specified in Section 19.5.3 with the
following addition:
1. Connectors should be exposed to a temperature of 125 (+0/-5 °C) for 30
minutes. Measurement should be made while the connectors are still in the
chamber at the specified temperature.
19.5.5 Dielectric Withstand Voltage (Sea Level) (see Section 19.4.8)
Unmated and mated connectors should be tested in accordance with Method
3001.1 of MIL-STD-1344. The following details and exceptions should apply:
1. The magnitude of the test voltage should be as specified in Table 19.4.8.
2. The test voltage should be applied between adjacent pairs of contacts and
between the shell and contacts adjacent to the shell.
3. A minimum of 20 signal contacts in each insert should be tested. The
location of the contacts should be selected such that measurements are
distributed to include the corners, sides, and center of the insert.
4. 100% of the power and coaxial contacts should be tested.
ARINC SPECIFICATION 600 – Page 110
ATTACHMENT 19
CONNECTOR SPECIFICATION
5. The test voltage should be maintained at the specified value for 60 seconds
minimum.
19.5.6 Dielectric Withstand Voltage (Altitude) (See Section 19.4.8)
Unmated and mated connectors should be tested as specified in Section 19.5.5 with
the following additions:
1. The leads of all test circuits should be brought out through the walls of the
chamber. There should be no wire splices inside the chamber.
2. The chamber should be evacuated to the altitude pressure equivalent
specified in Table 19.4.8.
19.5.7 Contact Resistance (See Section 19.4.9)
The contact resistance of mated contacts should be tested in accordance with
Method 3004.1 of MIL-STD-1344. The following details and exceptions should
apply:
1. A minimum of 20% of the signal contacts in each insert should be tested.
The location of the contacts should be selected such that there is an even
distribution of measurements across the insert.
2. 100% of the power contacts should be tested.
3. The voltage probes should be placed on the wires immediately behind the
contacts at their extremities where possible.
4. To facilitate testing, voltage probes may be so positioned as to include a
reasonable length of wire if the resistance of the wire is subtracted from the
value so obtained.
Table 19.5.1 – Performance Verification Tests
TEST
Examination of Product
Engaging Force (W/Contacts)
Low Level Circuit
Contact Resistance
Insulation Resistance (Ambient)
Insulation Resistance (Elevated)
DWV (Sea Level)
DWV (Altitude)
Maintenance Aging
Thermal Cycling
DWV (Sea Level)
Moisture Resistance
Insulation Resistance
Vibration
Shock
Durability
Low Level Circuit
Temperature Life
Insulation Resistance (Ambient)
SAMPLE GROUP
A
X
X
X
X
X
X
X
X
B
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
C
X
X
X
D
X
X
X
X
X
X
X
X
X
X
REQUIREMENT
PARAGRAPH
TEST
PARAGRAPH
19.4.5
19.4.10
19.4.9
19.4.6
19.4.7
19.4.8
19.4.8
19.4.12
19.4.11
19.4.8
19.4.14
19.4.6
19.4.15
19.4.16
19.4.17
19.4.10
19.4.18
19.4.6
19.5.2
19.5.8
19.5.7
19.5.3
19.5.4
19.5.5
19.5.6
19.5.10
19.5.9
19.5.5
19.5.11
19.5.3
19.5.12
19.5.13
19.5.14
19.5.8
19.5.15
19.5.3
ARINC SPECIFICATION 600 – Page 111
ATTACHMENT 19
CONNECTOR SPECIFICATION
TEST
DWV (Sea Level)
Contact Resistance
Salt Spray (Corrosion)
Contact Resistance
Engaging Force (W/ Contacts)
DWV (Sea Level)
Seal Leakage (Class B)
Contact Walk-Out (1 plug & 1
receptacle)
Contact Current Switching
Contact/Circuit Breaker Compatibility
Fluid Immersion
Contact Retention
Insert Retention
Examination of Product
SAMPLE GROUP
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
REQUIREMENT
PARAGRAPH
19.4.8
19.4.9
19.4.19
19.4.9
19.4.5
19.4.8
19.4.22
TEST
PARAGRAPH
19.5.5
19.5.7
19.5.16
19.5.7
19.5.2
19.5.5
19.5.19
19.4.24
19.5.21
19.4.25
19.4.26
19.4.27
19.4.21
19.4.20
19.5.22
19.5.23
19.5.24
19.5.12
19.5.17
19.5.8 Low Level Circuit (See Section 19.4.10)
The low-level contact resistance should be tested in accordance with Method
3002.1 of MIL-STD-1344 and the details and exceptions of Section 19.5.7.
Where possible, the voltage probes should be placed on the wires immediately
behind the contacts at their extremities. Care must be exercised to ensure that no
contaminates or oxides are present where the probes contact the wire.
19.5.9 Thermal Cycling (See Section 19.4.11)
Mated connectors should be tested in accordance with Method 1003 of
MIL-STD-1344 and the following detail:
1. Test condition B should apply.
2. The specimen should be allowed to return to room ambient conditions prior
to further tests.
19.5.10
Maintenance Aging (See Sections 19.4.12 and 19.4.13)
Connectors wired with suitable gauge wire should be tested in accordance with
Method 2002 of MIL-STD-1344. In addition, in each of 10 maintenance aging cycles
after installing all contacts, each connector should be mated and unmated 10 times.
The force required to insert and remove each contact in and from the connector
should be measured during the first and final cycles after the 10 connector matings
have been accomplished as discussed above.
19.5.11
Moisture Resistance (Humidity) (See Section 19.4.14)
Wire, mated connectors should be subjected to the humidity test specified in Method
1002.1 of MIL-STD-1344 with the following details and exceptions:
1. Type II (temperature cycling) should apply.
2. The mated connectors should be mounted in a horizontal position. There
should be no drip loops in the wires.
3. No polarizing voltage should be applied.
ARINC SPECIFICATION 600 – Page 112
ATTACHMENT 19
CONNECTOR SPECIFICATION
19.5.12
Vibration (See Section 19.4.15)
Mated connectors should be vibrated in accordance with MIL-STD-1344A, Method
2005.1. All contacts should be connected in series with 0.1 ampere max. flowing
through the contacts. Connectors should be held together by normal or method(s)
simulating normal means. Wires should be supported on a stationary frame not
closer than 8 inches from the connectors. The following details should apply:
1. Test condition “V”
2. Test condition letter “E”
3. 8 hours in each of three mutually perpendicular axes
19.5.13
Shock (Physical) (See Section 19.4.16)
Mated connectors should be subjected to the shock test in accordance with MILSTD-1344, Method 2004.1, Condition A. The shock test should be repeated three
times in each direction of the referenced 90-degree axis position (18 shocks total).
All contacts should be series wired and connected to a test circuit capable of testing
discontinuities of 1 microsecond and greater with 0.1 ampere max. flowing through
the contacts.
19.5.14
Durability (See Section 19.4.17)
Wire, assembled plugs, and receptacles should be subjected to 500 cycles of
mating and unmating (including electrical contact engagement) at a rate not to
exceed 250 ± 50 cycles per hour. Engagement and separation should be similar to
that encountered in service and may be accomplished by machine.
19.5.15
Temperature Life (See Section 19.4.18)
Wired, assembled, and mated connectors should be subjected to an ambient
temperature of 125 °C ± 3 °C for a period of 1000 hours. The sensing device used
to monitor temperature should be attached to the shell of the connector.
Contact resistance, insulation resistance, and dielectric withstand voltage tests
should be performed after the test samples have stabilized to room ambient
temperature.
19.5.16
Salt Spray (Corrosion) (See Section 19.4.19)
Wired, mated connectors should be tested in accordance with Method 1001 of MILSTD-1344 and the following details:
1. Test condition “B” should apply
2. Mated connectors should be unmated and cleaned per Method 1001 of MILSTD-1344 prior to further testing
19.5.17
Insert Retention (See Section 19.4.20)
Unwired connector halves should be tested in accordance with Method 2010 of MILSTD-1344 and the following details.
1. A uniformly distributed axial load of 35 psi should be applied to both faces of
each individual signal contact insert in shell sizes 1 and 2 (refer to
Figures 19-47 through 19-52).
ARINC SPECIFICATION 600 – Page 113
ATTACHMENT 19
CONNECTOR SPECIFICATION
2. A uniformly distributed axial load of 35 psi should be applied to both faces of
each signal contact insert contained within shell size 3 (refer to
Figures 19-47 through 19-52).
3. A uniformly distributed axial load of 75 psi should be applied to both faces of
each power and/or coaxial contacts insert for all shell sizes.
19.5.18
Contact Retention (See Section 19.4.21)
Contact retention should be tested in accordance with Method 2007 of
MIL-STD-1344. The following details and exceptions should apply.
1. The test should be applied to a minimum of 20% of the signal contacts and
100% of the power, coaxial, and fiber optic contacts.
2. The applicable load in Table 19.4.21 should be applied along the longitudinal
axis of the contacts in the direction tending to displace the contacts to the
rear of the insert.
3. The contacts which were subjected to maintenance aging should be selected
for contact retention.
4. Only the contacts selected need be installed in the connector.
19.5.19
Seal Leakage (See Section 19.4.22)
Fully wired and properly mated connector halves should be held vertically in a
fixture similar to the one shown in Figure 19.5.19. The wire bundles from the
connector should be routed so that a drip loop is created on each side of the
connector. The low part of the drip loops should be lower than the lowest part of the
connector. The fixture should be made to rotate at a speed of from 0.5 to 1.5 RPM.
The test fluid should be allowed to fall from approximately 100 0.1-inch diameter
holes in the bottom of a 6 inch diameter container located no higher than 6 inches
above the highest point of the connector. The test fluid should be a water solution
containing 5% by weight salt and 1% by weight liquid detergent and should be
circulated at a rate of from 2 to 4 gallons per minute. The solution should be at room
temperature and the ends of the wires should not be wetted.
The fixture should be operated for 1 hour after which the connector should be
subjected to the insulation resistance and dielectric withstand voltage tests defined
in 19.5.3 and 19.5.5. The connector should meet the requirements of 19.4.22
beginning within 5 minutes after termination of fluid exposure of the connector.
ARINC SPECIFICATION 600 – Page 114
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19.5.19 – Seal Leakage Test Fixture
19.5.20
Flexure-Bend (See Section 19.4.23)
This test is only applicable to contacts deviating from conventional pin and socket
technology. Two unmated connector halves (plug and receptacle) fully wired and
assembled (excluding backshell hardware) with 22 AWG size wire conforming to
MIL-W-22759/12C or MIL-W- 81381/12B should be suitably and individually
clamped to a fixture that is capable of rotating through 180° arc at a uniform rate.
The wire bundles should be in tension by applying a 5 pound weight as shown in
Figure 19.5.20. The mandrel size should be 10 times the diameter of the wire
bundle. Fifty (50) cycles of flexure should be performed in each of the two (2)
mutually perpendicular axes such that the most vulnerable areas to contact bend
damage are stressed. The clamp fixture should be rotated through an arc of 90° on
each side of vertical at a rate of 16 cycles per minute. A cycle should include
movement from the vertical to 90° left, then to 90° right and return to the vertical
position.
19.5.21
Contact Walk-Out (See Section 19.4.24)
Ten contacts in one plug and receptacle should be tested. The contacts should be
terminated to stranded steel cable of an appropriate size and installed in the
connector. The unmated connector should be mounted in a test fixture as shown in
Figure 19.5.21. A 3-pound load should be applied to the cable. One 360° rotation of
the fixture with the connector mounted should constitute one cycle. The connector
should be subjected to 100 cycles at a rate of 10 to 20 cycles per minute. Contact
cavities used in this test should be excluded from further testing.
ARINC SPECIFICATION 600 – Page 115
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19.5.20 – Flex-Band Test
19.5.22
Contact Current Switching (See Section 19.4.25)
This test is only applicable to contacts deviating from conventional pin and socket
technology. Five pairs of signal contacts selected randomly should be made to
break an inductive load a maximum of 10 times. Inductive load circuits should
consist of inductive and resistive load elements connected in series. The circuit
parameters should be 5 amperes, 115 volts, 400 Hz, and a 0.7 ± 0.05 lagging power
factor.
These contacts should not be subject to further testing.
19.5.23
Contact/Circuit Breaker Compatibility (See Section 19.4.26)
Five pairs of mated signal contacts terminated with 22 AWG wire should be
separately connected in series with a circuit breaker, power supply, and current
switching device. The circuit breaker trip-time should be verified prior to any testing
and tests should be conducted at 25 ºC ambient temperature.
The subject contacts should be subjected separately to 1 cycle of short circuit
current for the duration of the circuit breaker trip time. For the purpose of this test,
the short circuit current should be considered as 100% of rated contact current.
The following test equipment details apply:
a. The circuit breaker should conform to MIL-C-5809; part number MS 3320-5.
b. The power supply should deliver at least 50+ amps at 115 volts, 60 Hz.
c. The current switching device should be rated for the short circuit current.
These contacts should not be subject to further testing.
ARINC SPECIFICATION 600 – Page 116
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19.5.21 – Contact Walk-Out Test
19.5.24
Fluid Immersion (See Section 19.4.27)
a. Seals - The connector(s) in Groups B, C, and D (Class B only) should be
distributed such that one connector (mating plug and receptacle) should be
immersed in each fluid in Table 19.5.24 for the required time period. After
removal from the fluid the connector(s) should remain in free air per
Table 19.5.24 in a position to allow the fluid to drain from seal faces.
b. Retention Systems - The connectors in part (a) should be used. The
contacts should be removed and the unmated connectors should be
immersed in the same fluids as part (a) and specified in Table 19.5.24 for 20
hours at laboratory conditions. After removal, excess fluid should be allowed
to drain from each connector half for 4 hours prior to measurement of
contact retention forces (see Section 19.5.18) and insert retention (see
Section 19.5.17)
19.5.25
Contact Crimp Tensile Strength (See Section 19.4.28)
Contacts should be placed in a tensile testing machine and sufficient axial load
applied to pull the wire out of the contact or break the wire.
19.5.26
Axial Concentricity (See Section 19.4.29)
A minimum of 10 contacts of each type and size should be tested. After crimping to
wire, contacts should be checked in the area shown in Figure 19.5.26 and rotated
360º minimum. While the contact is rotated, the Total Indicator Reading (TIR)
should be measured at point A in Figure 19.5.26. Contacts which are end positioned
in the crimping tool should also be measured at point B in Figure 19.5.26.
ARINC SPECIFICATION 600 – Page 117
ATTACHMENT 19
CONNECTOR SPECIFICATION
Note: For size 12 and larger pins, X = 1 pin dia.
For pins smaller than size 12, X = 2 pin dia.
Figure 19.5.26 – Axial Concentricity
19.5.27
Contact Probe Damage (See Section 19.4.30)
Socket contacts should be subjected to the test of MIL-STD-1344, Method 2006.1
and the following detail.
1. A minimum of 3 contacts selected randomly in each insert should be tested.
The contacts should not have been subjected to other environmental tests
which could influence the test results.
19.5.28
Voltage Standing Wave Radio (VSWR)
The VSWR should be measured according to MIL-C-39012B (4.6.26).
19.5.29
Insertion Loss
The test method outlined in MIL-C-39012B (4.6.26) should be used to measure
insertion loss. The reference cable will consist of two short cables, each less than
12 inches long, connected together with TNC type connectors. The coaxial contacts
should be attached to cables of the same type and length as the reference cables.
The assembly of the coaxial contacts and cables should have the same electrical
length as the assembly of reference cables and connectors. The insertion loss will
be the increase in loss of the coaxial contact assembly compared to the reference
cable assembly.
19.6 Drawings (Figures)
The drawings identified as “Figures” in this section define the mechanical and
certain performance characteristics of the connectors.
COMMENTARY
All dimensions are given in inches with no metric equivalents due to
the critical nature of the dimensions and tolerances.
ARINC SPECIFICATION 600 – Page 118
ATTACHMENT 19
CONNECTOR SPECIFICATION
Table 19.5.24 – Fluids for Fluid Immersion Test
Sample
Number
Test Fluid
MIL-L-233699
1
MIL-H-5606
2
3
One part by volume of
isopropyl alcohol, per TT-I735, grade A or B, and
three parts by volume of
mineral spirits per TT-T291, grade 1 or P-D-680,
Type 1.
Test Procedures
Immerse unmated connectors in fluid at 120 ±3 °C for 5 minutes.
Remove connectors and allow to drain for a minimum of 1 hour at
room temperature. Fluid should be drained from all recesses.
Mate connectors and expose to 125 ± 3 °C in an air circulating
oven for 6 hours. Repeat procedure for a total of seven cycles.
Immerse unmated connectors in fluid at 85 ±3 °C for 5 minutes.
Remove connectors and allow to drain for a minimum of 1 hour at
room temperature. Fluid should be drained from all recesses.
Mate connectors and expose to 100 ±3 °C in an air circulating
oven for 6 hours. Repeat procedure for a total of seven cycles.
The wire, assembled, unmated connector should be immersed in
the fluid at 25 ±3 °C for 5 minutes, removed from the fluid and
exposed to free air for 24 ±2 hours. This conditioning cycle should
be repeated until the connector has been subjected to five
complete cycles. For a maximum of two cycles, the exposure to
free air may be extended to 75 hours.
ARINC SPECIFICATION 600 – Page 119
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 13.
Figure 19-41 – Shell Assembly Connector MCU Receptacle – Size 1
ARINC SPECIFICATION 600 – Page 120
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 13.
Figure 19-42 – Shell Assembly Connector Rack Plug – Size 1
ARINC SPECIFICATION 600 – Page 121
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 13.
ARINC SPECIFICATION 600 – Page 122
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-43 – Shell Assembly Connector MCU Receptacle – Size 2
Drawing updated by Supplement 13.
Figure 19-44 – Shell Assembly Connector Rack Plug – Size 2
ARINC SPECIFICATION 600 – Page 123
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 13.
Figure 19-45 – Shell Assembly Connector MCU Receptacle – Size 3
ARINC SPECIFICATION 600 – Page 124
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 13.
Figure 19-46 – Shell Assembly Connector Rack Plug – Size 3
ARINC SPECIFICATION 600 – Page 125
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-47 – Signal Contact Arrangement 01, Shell Size 1 Connector
ARINC SPECIFICATION 600 – Page 126
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-48 – Signal Contact Arrangement 02, Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 127
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y
4. With a positional tolerance of 0.004 diameter at maximum material
condition
5. Test voltage: 1500 Vrms
Drawing updated by Supplement 9.
Figure 19-49 – Contact Arrangement 05, Signal Contacts with Size 1 Coaxial
Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 128
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y.
4. With a positional tolerance of 0.004 diameter at maximum material
condition.
5. Test voltage: 1500 Vrms
Drawing updated by Supplement 9.
Figure 19-49.1 – Contact Arrangement 08, Signal Contacts with Size 1 Coaxial
Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 129
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. All dimensions are basic and in inches unless otherwise specified
2. Refer to intermateability drawings for location of datums X and Y
3. Contact cavities are to be located at true position with respect to
datums X and Y
4. With a positional tolerance of 0.004 diameter at maximum material
condition
5. Test voltage: 1500 Vrms
Figure 19-49.2 – Contact Arrangement 09, Size 1 Coaxial Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 130
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 9.
Figure 19.49.3 – Contact Arrangement 11, Size 1 Coaxial RF Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 131
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
Quantity
#8 Concentric Twinax
Or
# 8 Coaxial
10
Notes:
1. Concentic Twinax/Coax Contacts Shall be Grounded to the
Connector Plug and Receptacle Shells.
2. Base Insert Material Shall be Metallic.
Figure 19-49.4 – Contact Arrangement 12, Size 8 RF Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 132
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
Quantity
#8 Concentric Twinax
Or
#8 Coaxial
6
Notes:
1. Concentic Twinax/Coax Contacts Shall be Grounded to the
Connector Plug and Receptacle Shells.
2. Base Insert Material Shall be Metallic.
Figure 19-49.5 – Contact Arrangement 13, Size 8 RF Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 133
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#22 Signal
#8 Concentric Twinax
Or
Coaxial
Quantity
118
2
Note:
1. Concentric Twinax/Coax Contacts shall be grounded to the
Connector Plug and Receptacle Shells.
Figure 19-46.6A – Contact Arrangement 14, Size 8 RF and Size 22 Signal
Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 134
ATTACHMENT 19
CONNECTOR SPECIFICATION
Plug Front Engaging Face
Figure 19-49.6B – Contact Arrangement 14, Size 8 RF and Size 22 Signal
Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 135
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#22 Signal
#20 Power
#16 Power
Quantity
110
6
5
Figure 19-49.7A – Contact Arrangement 15, Size 16 and 20 Power, Size 22
Signal Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 136
ATTACHMENT 19
CONNECTOR SPECIFICATION
Plug Front Engaging Face
Figure 19-49.7B – Contact Arrangement 15, Size 16 and 20 Power, Size 22
Signal Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 137
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#20 Power
#16 Power
Quantity
24
10
Figure 19-49.8 – Contact Arrangement 16, Size 16 and 20 Power Shell Size 2 and 3
Connectors
ARINC SPECIFICATION 600 – Page 138
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#20 Power
Quantity
60
Figure 19.49.9 – Contact Arrangement 17, Size 20 Power Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 139
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#8 Power
Quantity
6
Figure 19-49.10 – Contact Arrangement 18, Size 8 Power Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 140
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#22 Signal
Quantity
40
Note: Alignment groove is on Top of Insert for Receptacle Shell and
Bottom of Insert for Plug Shell.
Figure 19-49.11 – Contact Arrangement 19, Size 22 Signal Shell Size 1 Connector
ARINC SPECIFICATION 600 – Page 141
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#22 Signal
#8 Concentric
Twinax
Or
Coaxial
Quantity
28
2
Figure 19-49.12A – Contact Arrangement 20, Size 8 Coaxial RF and Size 22
Signal Shell Size 1 Connector
ARINC SPECIFICATION 600 – Page 142
ATTACHMENT 19
CONNECTOR SPECIFICATION
Plug Front Engaging Face
Figure 19.49.12B – Contact Arrangement 20, Size 8 Coaxial RF and Size 22
Signal Shell Size 1 Connector
ARINC SPECIFICATION 600 – Page 143
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#12 Power
Quantity
4
Note: Alignment groove is on top of Insert for Receptacle Shell and
Bottom of Insert for Plug Shell.
Figure 19-49.13 – Contact Arrangement 21, Size 12 Power Shell Size 1 Connector
ARINC SPECIFICATION 600 – Page 144
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Contact Style
#12 Signal
#16 Power
#12 Power
Quantity
50
5
4
Figure 19-49.14A – Contact Arrangement 22, Size 12 and 16 Power Size 22
Signal Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 145
ATTACHMENT 19
CONNECTOR SPECIFICATION
Plug Front Engaging Face
Figure 19-49.14B – Contact Arrangement 22, Size 12 and 16 Power Size 22
Signal Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 146
ATTACHMENT 19
CONNECTOR SPECIFICATION
Receptacle Front Engaging Face
Number of
Contacts
100
5
5
Contact Size
#22 Signal
#20 Power
#12 Power
Cavity
Location
A1 thru K10
101 thru 105
106 thru 110
Figure 19-45.15A – Contact Arrangement 23, Size 12 and 20 Power, Size 22
Signal Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 147
ATTACHMENT 19
CONNECTOR SPECIFICATION
Plug Front Engaging Face
Figure 19-49.15B – Contact Arrangement 23, Size 12 and 20 Power, Size 22
Signal Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 148
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing added by Supplement 15.
Number of
Contacts
100
5
5
Contact Size
#22 Signal
#20 Power
#12 Power
Cavity
Location
A1 thru K10
101 thru 105
106 thru 110
Figure 19-49.16 – Contact Arrangement 20F12T8/20F12Q8
ARINC SPECIFICATION 600 – Page 149
ATTACHMENT 19
CONNECTOR SPECIFICATION
[1.037]
26.34
REF
[0.420]
10.68
0.05 [0.002] X Y
[0.105]
2.67
[0.315]
8.01
[0.210]
5.34
0.05 [0.002] X Y
[0.030]
0.76
[1.087]
27.61
REF
[0.319]
8.10
[0.189]
4.80
Keyway
[0.120]
3.05
3 cavities for #16
Electrical contact
[0.449]
11.40
[0.340]
8.64
2 cavities for #8 quadrax contacts.
Contact body is grounded to the
Connector shell.
0.05 [0.002] X Y
[0.315]
8
Angular position of the
optical contact polarization
key.
RECEPTACLE
REAR FACE
PLUG
REAR FACE
PLUG
FRONT FACE
[inches]
mm
Drawing added by Supplement 15.
Number of
Contacts
12
3
2 (Plug)
Contact Size
16 (Optical Termini)
16 (Electrical)
8 (Quadrax)
Insert Cavity
Location
1 thru 12
13 thru 15
16 thru 17
Figure 19-49.17 – Contact Arrangement 17F12Q2
ARINC SPECIFICATION 600 – Page 150
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing added by Supplement 15.
Number of
Contacts
Contact Size
Insert Cavity
Location
36
16 (Optical Contact)
RR/RR
1 thru 36
Figure 19-49.18 – Contact Arrangement 36F36
ARINC SPECIFICATION 600 – Page 151
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing added by Supplement 15.
Number of
Contacts
4
1
2 (Plug)
5
Contact Size
12 (Electrical)
16 (Electrical)
5 (Coaxial)
16 (Optical Termini)
Insert Cavity
Location
1 thru 4
5
6 thru 7
8 thru 12
Figure 19-49.19 – Contact Arrangement 12F5C2
ARINC SPECIFICATION 600 – Page 152
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-50 – Cavity Detail, Pin Front Insulator, Signal Contact
ARINC SPECIFICATION 600 – Page 153
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y within a positional tolerance of 0.004 diameter at
maximum material condition.
Figure 19-51 – Power Coaxial Contact Arrangement 03, Shell Size 1
ARINC SPECIFICATION 600 – Page 154
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y within a positional tolerance of 0.004 diameter at
maximum material condition.
Figure 19-52 – Power Coaxial Contact Arrangement 04, Shell Size 2 and 3
ARINC SPECIFICATION 600 – Page 155
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y within a positional tolerance of 0.004 diameter at
maximum material condition.
4. Test voltage: 1,500 Vrms
Figure 19-52.1 – Signal Arrangement 07, Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 156
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y within a positional tolerance of 0.004 diameter at
maximum material condition.
4. Test voltage: 1,500 Vrms
5. Refer to Figures 19-69.2 and 19-70.2 for contact mating tips
dimensions for insert 85 (arrangement 10).
Figure 19-52.2 – Signal and Power Contact Arrangement 10, Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 157
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 10.
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y within a positional tolerance of 0.004 diameter at
maximum material condition.
4. Test voltage: 1,500 Vrms
Figure 19-52.3 – Contact Arrangement 24, Size 8 RF & Size 20
Power Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 158
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 10.
Notes:
1. All dimensions are basic and in inches unless otherwise specified.
2. Refer to intermateability drawings for location of datums X and Y.
3. Contact cavities are to be located at true position with respect to
datums X and Y within a positional tolerance of 0.004 diameter at
maximum material condition.
4. Test voltage: 1,500 Vrms
Figure 19-52.4 – Contact Arrangement 25, Size 1 Coaxial Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 159
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing/Notes updated by Supplement 11.
Figure 19-52.5A – Contact Arrangement 26, Size 20 HD and Size 22
Shell Size 2 and 3 Connectors
ARINC SPECIFICATION 600 – Page 160
ATTACHMENT 19
CONNECTOR SPECIFICATION
RECEPTACLE
NUMBER OF CONTACTS
4 (PIN)
80 (SOCKET)
CONTACT SIZE
20HD
22
INSERT CAVITY LOCATION
1, 4, 5, & 6
A5 THRU A10
B5 THRU B10
C1 THRU G10
H5 THRU H10
J5 THRU J10
K5 THRU K10
Notes 1 and 2 define standard receptacle and plug inserts having rear release/rear
remove contacts. Note 3 define a receptacle insert having front release signal
contacts.
Notes:
1. Receptacle Insert and Contacts – key dimensions relative to Datum
M*
Insert Face
-0.027
-0.013
Contact Mating Tips
Size 22 Socket
+0.292
+0.268
Size 20HD Pin
+0.372
+0.322
2. Plug Insert and Contacts – key dimensions relative to Datum M*
Insert Face
-0.019
-0.005
Contact Mating Tips
Size 22 Pin
+0.088
+0.048
Size 20 Socket
+0.099
+0.057
3. Receptacle Insert for front release signal contacts Positions
Insert face and contact mating tips: Same
positions relative to Datum M as in Note 1.
Contact Types
Size 20HD
Crimp pin, rear release/rear remove
Size 22
Wire wrap or solder tail* socket, front
release/front remove
Rear protrusion
Insert rear protrusion past the insert
retaining plates shall not exceed 0.120
*
Datum M is shown in ARINC Specification 600 Page 159 on
Receptacle Front face.
*
When using solder tail contacts for a circuit board mounted
close to the rear of the connector, contacts not having the
optional shoulder at the base of the solder tail are required.
Drawing/Notes updated by Supplement 11.
ARINC SPECIFICATION 600 – Page 161
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-52.5B – Contact Arrangement 26, Size 20 HD and Size 22
Shell Size 2 and 3 Connectors
Drawing/Notes updated by Supplement 11.
Figure 19-52.6 – Contact Arrangement 27, Size 5 Coaxial 1, Shell Size 1 Connectors
ARINC SPECIFICATION 600 – Page 162
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing/Notes updated by Supplement 11.
Figure 19-52.7- Contact Arrangement 28, Size 16 and Size 12, Shell Size 2 and 3 Contacts
ARINC SPECIFICATION 600 – Page 163
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1.
2.
3.
4.
5.
Contact will accommodate No. 22, No. 24, or No. 26 wire.
Use M22520/2-01 crimp tool with M22520/2-23 locator
Use CIT-DPKMA22-1 insert tool with M22520/2-23 locator
Electrical engagement point
Finish:
Gold per MIL-G-45204, type I or II, grade C or D
class 1 (50 micro inches min.) over ductile nickel
underplate of 40 to 75 micro inches per QQ-N-290
over a copper flash
6. Material:
Copper Alloy
Figure 19-53 – Signal Contact, Pin, Size 2222, Low Insertion Force
ARINC SPECIFICATION 600 – Page 164
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-54 – Signal Contact Assembly, Socket, Size 2222, Low Insertion Force
ARINC SPECIFICATION 600 – Page 165
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-54.1 – Signal Contact Assembly, Socket, Size 2222, Low Insertion Force, P.C. Post
0.025 Diameter
ARINC SPECIFICATION 600 – Page 166
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-54.2 – Contacts, Electric, Coaxial, Socket, Crimp, Size 1
ARINC SPECIFICATION 600 – Page 167
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-54.3 – Contacts, Electric, Coaxial, Pin, Crimpable, Size 1
ARINC SPECIFICATION 600 – Page 168
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-54.4 – Contact, Electric, Coaxial, Pin, Clamp, Size 1 RF
ARINC SPECIFICATION 600 – Page 169
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-54.5 – Contact, Electric, Coaxial, Pin, Clamp, Size 1 RF
ARINC SPECIFICATION 600 – Page 170
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-54.6-1 – Contact, Electric, Coaxial, Pin, Clamp, Size 1 RF
ARINC SPECIFICATION 600 – Page 171
ATTACHMENT 19
CONNECTOR SPECIFICATION
RECOMMENDED STRIP LENGTHS (CRIMP TERMINATION)
(See Table 1 for Cable Dimensions)
Notes:
1.
2.
3.
4.
5.
Unless otherwise specified, dimensions are in inches.
Dimensions shown apply after plating.
This contact Intended to be nonreleasable.
Design optional, see TABLE 1 for approved cable size.
See TABLE 2 for hex crimp size.
REQUIREMENTS:
Materials:
Body components:
Brass, 1/2 HD, per QQ-B-626
Center Contact:
Beryllum Copper per QQ-C-530
Crimp Ferrule:
Copper, annealed
Dielectric:
Teflon per MIL-P-19468
Heat Shrink Tubing:
Plating, Body & Center Contact: Gold per NIL-G-45204
Crimp Ferrule, Tin per ASTH-B-545
TYPE II, Grade Cord, Class 1, 50 Micro inch Minimum over nickel plating, per QQ-N-290, 50
Micro Inch Minimum
Performance:
Temperature range:
Impedance:
Frequency range:
Insertion Loss:
Contact Resistance:
-65 ºC to 165 ºC
50 ohm nominal
0-2 GHz
0.3 Db
0.2 milliohms max (body)
1.0 milliohms max (center contact)
Insulation Resistance:
5000 megohms minimum
Dielectric withstanding voltage: 2500 Vrms at sea level (RG214)
Insertion Force:
1 lbs. max with .094 pin
Withdrawl Force:
2 oz. min with .092 pin
Tooling:
The contacts covered by this specification shall be crimped using the recommended tooling
called out by TABLE 2 or equivalent. Center contacts may be soldered or crimped. If crimped
use military tool M22520/5-01 with the appropriate die set or M22520/1-01 indent tool.
Figure 19-54.6-2 – Recommended Strip Lengths (Crimp Termination)
ARINC SPECIFICATION 600 – Page 172
ATTACHMENT 19
CONNECTOR SPECIFICATION
RG214/U
RG142/U
RG393/U
AA-5886 TIMES
AA-5887 TIMES
AA-5888-TIMES
311201 ECS
CABLE
Cable Dimensions (Table 1)
M17/75-RG214
M17/60-RG142
M17/127-RG393
N/A
N/A
N/A
N/A
MILITARY P/N
RG214/U
RG142/U
RG393/U
AA-5886 TIMES
AA-5887 TIMES
AA-5888 TIMES
311201 ECS
CABLE
Tooling (Table 2)
M22520/2-01
M22520/2-01
M22520/2-01
M22520/2-01
M22520/2-01
M22520/2-01
M22520/2-01
MILITARY TOOL
M17/75-RG214
M17/60-RG142
M17/127-RG393
N/A
N/A
N/A
N/A
MILITARY P/N
0.425
0.195
0.390
0.390
0.270
0.230
0.320
01
0.285
0.116
0.285
0.285
0.185
0.146
0.237
02
M22520/5-25, /5-61
M22520/5-11, /5-19, /5-57
M22520/5-25, /5-61
M22520/5-25, /5-61
M22520/5-29, /5-35, /5-55
M22520/5-11, /5-19, /5-57
M22520/5-29, /5-35, /5-55
MILITARY DIE
0.089
0.037
0.094
0.105
0.068
0.054
0.089
03
0.429
0.213
0.429
0.429
0.324
0.213
0.324
HEX SIZE
Figure 19-54.6-3 – Contacts, Electric, Coaxial, Socket Crimp, Size 1 RF Tooling
ARINC SPECIFICATION 600 – Page 173
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-55 – Power Contact, Pin, Size 2020 HD, Low Insertion Force
ARINC SPECIFICATION 600 – Page 174
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-56 – Power Contact Assembly, Socket, Size 2020 HD, Low Insertion Force
ARINC SPECIFICATION 600 – Page 175
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-57 – Power Contact, Pin, Size 1616 HD, Low Insertion Force
ARINC SPECIFICATION 600 – Page 176
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-58 – Power Contact Assy, Socket, Size 1616 HD, Low Insertion Force
ARINC SPECIFICATION 600 – Page 177
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-59 – Power Contact, Pin, Size 1212 HD, Low Insertion Force
ARINC SPECIFICATION 600 – Page 178
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-60 – Power Contact Assy, Socket, Size 1212 HD, Low Insertion Force
ARINC SPECIFICATION 600 – Page 179
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions in inches
2. Dimensions shown apply after plating
Requirements:
Materials:
Body components: Brass 1/2 HD per QQ-B-626
Beryllium per QQ-C-530
Insulators:
Per MIL-P 19468A
Crimp ferrule:
Copper, annealed
Gaskets:
Silicone rubber per ZZ-R-765
Plating:
Gold per MIL-G-45204
Dash No.
-001
-002
Table 1
Cable
Cable
Size
Retention
RG-58C
60 lb
RG-223
60 lb
Remarks
Straight exit
Straight exit
Performance:
Temperature range: -65 °C to +165 °C
Impedance:
50 ohms nominal
Rated voltage:
325 Vrms at sea level
Frequency range: 0-500 MHz VSWR 1-30: 1
1500-1700 MHz VSWR 1.50: 1
Contact resistance: 1.0 milliohm (body)
2.1 milliohms (center)
Insulation resistance: 5,000 megohms minimum
Dielectric withstand voltage: 750V ns at sea level
Tooling:
The contacts covered by this standard should be installed with the tools recommended by the
qualified contact producer and in accordance with the contact producer's recommendation.
Table 1
Drawing updated by Supplement 11.
Figure 19-60.1 – Contacts, Electric, Coaxial, Socket, Crimp, Size 5
ARINC SPECIFICATION 600 – Page 180
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions in inches
2. Dimensions shown apply after plating
Requirements:
Materials:
Body components: Brass 1/2 HD per QQ-B-626
Beryllium per QQ-C-530
Insulators:
Per MIL-P 19468A
Crimp ferrule:
Copper, annealed
Gaskets:
Silicone rubber per ZZ-R765
Plating:
Gold per MIL-G-45204
Dash No.
-001
-002
Table 1
Cable
Cable
Size
Retention
RG-58C
60 lb
RG-223
60 lb
Remarks
Straight exit
Straight exit
Performance:
Temperature range: -65 °C to +165 °C
Impedance:
50 ohms nominal
Rated voltage:
325 Vrms at sea level
Frequency range: 0-500 MHz VSWR 1-30: 1
1500-1700 MHz VSWR 1.50: 1
Contact resistance: 1.0 milliohm (body)
2.1 milliohms (center)
Insulation resistance:
5,000 megohms minimum
Dielectric withstand voltage: 750V ns at sea level
Tooling: The contacts covered by this standard should be installed with the tools recommended
by the qualified contact producer and in accordance with the contact producer's
recommendation.
Figure 19-60.2 – Contacts, Electric, Coaxial, Socket, Crimp, Size 5
ARINC SPECIFICATION 600 – Page 181
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-61 – Post, Polarizing
ARINC SPECIFICATION 600 – Page 182
ATTACHMENT 19
CONNECTOR SPECIFICATION
TO BE ADDED
CONTACT, ELECTRIC SIGNAL, FIXED POSITION
RECTANGULAR, TERMINATION POSTS, PLUG
Figure 19-62 – Contact, Electric Signal, Fixed Position Rectangular, Termination Posts, Plug
ARINC SPECIFICATION 600 – Page 183
ATTACHMENT 19
CONNECTOR SPECIFICATION
TO BE ADDED
CONTACT, ELECTRIC SIGNAL, FIXED POSITION
RECTANGULAR, TERMINATION POSTS, PLUG
Figure 19-63 – Contact, Electric Signal, Fixed Position Rectangular, Termination Posts, Plug
ARINC SPECIFICATION 600 – Page 184
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-63.1 – Signal Contact Assembly, Socket, Front Release, Size 2222, Low Insertion
Force
ARINC SPECIFICATION 600 – Page 185
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 8, and 10 updated by Supplement 18.
Figure 19-67 – Intermateability, Shell Size 1 – Receptacle
ARINC SPECIFICATION 600 – Page 186
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 7, and 12 updated by Supplement 18.
Figure 19-68 – Intermateability, Shell Size 1 – Plug
ARINC SPECIFICATION 600 – Page 187
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 8, and 10 updated by Supplement 18.
Figure 19-69 – Intermateability, Shell Size 2 – Receptacle
ARINC SPECIFICATION 600 – Page 188
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 8, and 11 updated by Supplement 18.
Figure 19-69.1 – Intermateability, Shell Size 2 – Receptacle with Size 1 Coax
ARINC SPECIFICATION 600 – Page 189
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 8, and 10 updated by Supplement 18.
Note 11 added by Supplement 19.
Figure 19-69.2 – Intermateability, Shell Size 2 – Receptacle with Size 1 Coax
ARINC SPECIFICATION 600 – Page 190
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 7, and 12 updated by Supplement 18.
Figure 19-70 – Intermateability, Shell Size 2 Plug
ARINC SPECIFICATION 600 – Page 191
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 7, and 12 updated by Supplement 18.
Figure 19-70.1 – Intermateability, Shell Size 2 – Plug with Size 1 Coax
ARINC SPECIFICATION 600 – Page 192
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 7, and 12 updated by Supplement 18.
Note 13 added by Supplement 19.
Figure 19-70.2 – Intermateability, Shell Size 2 – Plug with Size 1 Coax
ARINC SPECIFICATION 600 – Page 193
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 13.
Figure 19-70.3 – Intermateability, Shell Size 3 – Plug with Size 1 RF Coax
ARINC SPECIFICATION 600 – Page 194
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 8, and 12 updated by Supplement 18.
Figure 19-71 – Intermateability, Shell Size 3 – Receptacle
ARINC SPECIFICATION 600 – Page 195
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes 5, 7, and 13 updated by Supplement 18.
Figure 19-72 – Intermateability, Shell Size 3 – Plug
ARINC SPECIFICATION 600 – Page 196
ATTACHMENT 19
CONNECTOR SPECIFICATION
Table 19.6.2 – Intermateability Dimensions
Size 1 connector
Receptacle
Plug
Horiz
Vertical
Signal
Power
Signal
Power
1 insert
2 inserts
Signal
Power
All
sizes
vertical
top to
bottom
Size 2 connector
Horiz
Vertical
Size 3 connector
Horizontal
Vertical
Without ribs
max at plane Z
0.691
3.431
1.339
1.291
3.431
1.339
1.291
2.751
3.431
1.339
5.610
Max over ribs
at plane Y
0.698
3.438
1.348
1.298
3.438
1.348
1.298
2.758
3.438
1.348
5.618
Width of plug
at plane N
0.691
0.687
3.431
3.427
1.339
1.335
1.291
1.287
3.431
3.427
1.339
1.335
1.291
1.287
2.751
2.747
3.431
3.427
1.339
1.335
5.610
5.606
Receptacle
min at plane X
0.696
3.436
1.346
1.296
3.436
1.346
1.296
2.756
3.436
1.346
5.616
Receptacle
width at edge
of chamfer
0.701
0.697
3.441
3.437
1.353
1.349
1.301
1.297
3.441
3.437
1.353
1.349
1.303
1.299
2.761
2.757
3.441
3.437
1.353
1.349
5.622
5.618
Figure 19-72.1 – Intermateability Details
ARINC SPECIFICATION 600 – Page 197
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-72.2 – Shell Size 2 and 3 Plug Shell Modification
ARINC SPECIFICATION 600 – Page 198
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-72.3 – Outline, Waveguide Connection
ARINC SPECIFICATION 600 – Page 199
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-72.4 – Waveguide Connection, Rack (Arrangement 06)
ARINC SPECIFICATION 600 – Page 200
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-72.5 – Waveguide Connection, Box (Arrangement 06)
ARINC SPECIFICATION 600 – Page 201
ATTACHMENT 19
CONNECTOR SPECIFICATION
Figure 19-72.6 – Shell Assembly, Receptacle, Size 2, Float Mount
ARINC SPECIFICATION 600 – Page 202
ATTACHMENT 19
CONNECTOR SPECIFICATION
Table 19.6.3
Allowable Contact Cavity T.P. Location with Respect to
Horizontal and Vertical Shell Dimensions
Plug, Shell Size 1
Length
(-R-)
3.4310
3.4305
3.4300
3.4295
3.4290
3.4285
3.4280
3.4275
3.4270
0.6910
0.6905
0.6900
0.6895
Width (-V-)
0.6890
0.6885
0.6880
0.0087
0.0083
0.0079
0.0075
0.0090
0.0087
0.0084
0.0081
0.0077
0.0073
0.0069
0.0089
0.0086
0.0083
0.0080
0.0077
0.0073
0.0070
0.0066
SEE NOTE
0.0085
0.0082
0.0089
0.0084
0.0080
0.0090
0.0086
0.0082
0.0078
0.0087
0.0084
0.0080
0.0076
0.0072
0.6875
0.0086
0.0085
0.0082
0.0079
0.0076
0.0073
0.0070
0.0066
0.0062
0.6870
0.0082
0.0080
0.0078
0.0075
0.0072
0.0069
0.0066
0.0062
0.0060
0.7005
0.0086
0.0085
0.0082
0.0079
0.0076
0.0073
0.0070
0.0066
0.0062
0.7010
0.0082
0.0080
0.0078
0.0075
0.0072
0.0069
0.0066
0.0062
0.0060
Table 19.6.4
Allowable Contact Cavity T.P. Location with Respect to
Horizontal and Vertical Shell Dimensions
Receptacle, Shell Size 1
Length
(-R-)
3.4370
3.4375
3.4380
3.4385
3.4390
3.4395
3.4400
3.4405
3.4410
0.670
0.6975
0.6980
0.6985
Width (-V-)
0.6990
0.6995
0.7000
0.0087
0.0083
0.0079
0.0075
0.0090
0.0087
0.0084
0.0081
0.0077
0.0073
0.0069
0.0089
0.0086
0.0083
0.0080
0.0077
0.0073
0.0070
0.0066
SEE NOTE
0.0085
0.0082
0.0089
0.0084
0.0080
0.0090
0.0086
0.0082
0.0078
0.0087
0.0084
0.0080
0.0076
0.0072
NOTE: IN AREA LEFT BLANK, MAXIMUM ALLOWABLE T.P. IS 0.009.
Figure 19-72.7 – Allowable Size 22 Contact Cavity True Position Diameter, Shell Size 1
ARINC SPECIFICATION 600 – Page 203
ATTACHMENT 19
CONNECTOR SPECIFICATION
Table 19.6.5
Allowable Contact Cavity T.P. Location with Respect to
Horizontal and Vertical Shell Dimensions
Plug, Shell Size 2
Length
(-R-)
3.4310
3.4305
3.4300
3.4295
3.4290
3.4285
3.4280
3.4275
3.4270
1.2910
1.2905
1.2900
1.2895
Width (-V-)
1.2890
1.2885
1.2880
0.0087
0.0083
0.0079
0.0075
0.0090
0.0087
0.0084
0.0081
0.0077
0.0073
0.0069
0.0089
0.0086
0.0083
0.0080
0.0077
0.0073
0.0070
0.0066
SEE NOTE
0.0085
0.0082
0.0089
0.0084
0.0080
0.0090
0.0086
0.0082
0.0078
0.0087
0.0084
0.0080
0.0076
0.0072
1.2875
0.0086
0.0085
0.0082
0.0079
0.0076
0.0073
0.0070
0.0066
0.0062
1.2870
0.0082
0.0080
0.0078
0.0075
0.0072
0.0069
0.0066
0.0062
0.0060
1.3005
0.0086
0.0085
0.0082
0.0079
0.0076
0.0073
0.0070
0.0066
0.0062
1.3010
0.0082
0.0080
0.0078
0.0075
0.0072
0.0069
0.0066
0.0062
0.0060
Table 19.6.6
Allowable Contact Cavity T.P. Location with Respect to
Horizontal and Vertical Shell Dimensions
Receptacle, Shell Size 2
Length
(-R-)
3.4370
3.4375
3.4380
3.4385
3.4390
3.4395
3.4400
3.4405
3.4410
1.2970
1.2975
1.2980
1.2985
Width (-V)
1.2990
1.2995
1.3000
0.0087
0.0083
0.0079
0.0075
0.0090
0.0087
0.0084
0.0081
0.0077
0.0073
0.0069
0.0089
0.0086
0.0083
0.0080
0.0077
0.0073
0.0070
0.0066
SEE NOTE
0.0085
0.0082
0.0089
0.0084
0.0080
0.0090
0.0086
0.0082
0.0078
0.0087
0.0084
0.0080
0.0076
0.0072
NOTE: IN AREA LEFT BLANK, MAXIMUM ALLOWABLE T.P. IS 0.009.
Figure 19-72.8 – Allowable Size 22 Contact Cavity True Position Diameter, Shell Size 2
ARINC SPECIFICATION 600 – Page 204
ATTACHMENT 19
CONNECTOR SPECIFICATION
Table 19.6.7
Allowable Contact Cavity T.P. Location with Respect to
Horizontal and Vertical Shell Dimensions
Plug, Shell Size 3
Length
(-R-)
3.4310
3.4305
3.4300
3.4295
3.4290
3.4285
3.4280
3.4275
3.4270
2.7510
2.7505
2.7500
2.7495
Width (-V-)
2.7490
2.7385
2.7480
0.0087
0.0083
0.0079
0.0075
0.0090
0.0087
0.0084
0.0081
0.0077
0.0073
0.0069
0.0089
0.0086
0.0083
0.0080
0.0077
0.0073
0.0070
0.0066
SEE NOTE
0.0085
0.0082
0.0089
0.0084
0.0080
0.0090
0.0086
0.0082
0.0078
0.0087
0.0084
0.0080
0.0076
0.0072
2.7475
0.0086
0.0085
0.0082
0.0079
0.0076
0.0073
0.0070
0.0066
0.0062
2.7470
0.0082
0.0080
0.0078
0.0075
0.0072
0.0069
0.0066
0.0062
0.0060
2.7605
0.0086
0.0085
0.0082
0.0079
0.0076
0.0073
0.0070
0.0066
0.0062
2.7610
0.0082
0.0080
0.0078
0.0075
0.0072
0.0069
0.0066
0.0062
0.0060
Table 19.6.8
Allowable Contact Cavity T.P. Location with Respect to
Horizontal and Vertical Shell Dimensions
Receptacle, Shell Size 3
Length
(-R-)
3.4370
3.4375
3.4380
3.4285
3.4390
3.4395
3.4400
3.4405
3.4410
2.7570
2.7575
2.7580
2.7585
Width (-V-)
2.7590
2.7595
2.7600
0.0087
0.0083
0.0079
0.0075
0.0090
0.0087
0.0084
0.0081
0.0077
0.0073
0.0069
0.0089
0.0086
0.0083
0.0080
0.0077
0.0073
0.0070
0.0066
SEE NOTE
0.0085
0.0082
0.0089
0.0084
0.0080
0.0090
0.0086
0.0082
0.0078
0.0087
0.0084
0.0080
0.0076
0.0072
NOTE: IN AREA LEFT BLANK, MAXIMUM ALLOWABLE T.P. IS 0.009.
Figure 19-72.9 – Allowable Size 22 Contact Cavity True Position Diameter, Shell Size 3
ARINC SPECIFICATION 600 – Page 205
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating.
Requirements:
Materials:
Body components
Insulator
Crimp ferrule
Center contact
Plating
Beryllium copper per ASTM-B-196
PTFE per ASTM-D-1710
Brass per QQ-B-626
Brass per QQ-B-626
Gold per AMS 2922, 50 microinches minimum over 50 microinches
nickel underplate per QQ-N-290
Performances:
-65 °C to +125 °C.
75 Ω nominal
325 Vrms at sea level.
0 to 500 MHz
1.30:1
10 mΩ max (center)
1.5 mΩ max (outer body)
Insulation resistance 5000 MΩ min.
D.W.V
750 Vrms at sea level.
Tensile Strength
The size 5 contact below is similar to that described in
MILC-39029/99A. The user should refer to the guidance
regarding tensile strength provided in that document.
Temperature range
Impedance
Rated voltage
Frequency range
V.S.W.R
Contact resistance
Tooling:
Insertion/Extraction Tool with M81969/28-01
Crimping Tool:
Center Contact
Outer Body
M22520/2-01 with locator recommended by the contact
manufacturer.
M22520/5-01 with die M22520/5-05.
ARINC SPECIFICATION 600 – Page 206
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 14.
Figure 19-73.1 – Contacts, Electrical, Coaxial, Pin, Size 5, 75 Ohms
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating.
Requirements:
Materials:
Body components
Insulator
Crimp ferrule
Center contact
Plating
Brass per QQ-B-626
PTFE per ASTM-D-1710
Brass per QQ-B-626
Beryllium copper per ASTM-B-196
Gold per AMS 2422, 50 microinches, minimum over 50 microinches
nickel underplate per QQ-N-290
Performances:
-65 °C to +125 °C.
75 Ω nominal
325 Vrms at sea level.
0 to 500 MHz
1.30:1
10 mΩ max (center)
1.5 mΩ max (outer body)
Insulation resistance 5000 MΩ min.
D.W.V
750 Vrms at sea level.
Tensile Strength
The size 5 contact below is similar to that described in
MIL-C-39029/99A. The user should refer to the guidance regarding
tensile strength provided in that document.
Temperature range
Impedance
Rated voltage
Frequency range
V.S.W.R
Contact resistance
Tooling
Insertion/Extraction Tool with M181969/28-01
Crimping Tool:
ARINC SPECIFICATION 600 – Page 207
ATTACHMENT 19
CONNECTOR SPECIFICATION
Center Contact
Outer Body
M22520/2-01 with locator recommended by the manufacturer
M22520/5-01 with die M22520/5-05
Drawing updated by Supplement 14.
Figure 19-73.2 – Contacts, Electrical, Coaxial, Socket, Size 5, 75 Ohms
ARINC SPECIFICATION 600 – Page 208
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating.
Requirements:
Materials:
Body components
Insulator
Crimp ferrule
Center contact
Plating
Beryllium copper per ASTM-B-196
PTFE per ASTM-D-1710
Brass per QQ-B-626
Brass per QQ-B-626
Gold per AMS per 2422, 50 microinches, minimum over 50
microinches nickel underplate per QQ-N-290
Performances:
-65 °C to +125 °C.
75 Ω nominal
325 Vrms at sea level.
0 to 500 MHz
1.30:1
10 mΩ max (center)
1.5 mΩ max (outer body)
Insulation resistance 5000 MΩ min.
D.W.V
750 Vrms at sea level.
Tensile Strength
The size 8 contact below is similar to that described in
MIL-C-39029/59D. The user should refer to the guidance regarding
tensile strength provided in that document
Temperature range
Impedance
Rated voltage
Frequency range
V.S.W.R
Contact resistance
Tooling:
Insertion/Extraction Tool with M81969/28-01
Crimping Tool:
Center Contact
Outer Body
M22520/2-01 with locator recommended by the contact manufacturer
M22520/5-01 with die M22520/5-05
ARINC SPECIFICATION 600 – Page 209
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 14.
Figure 19-74.1 – Contacts, Electrical, Coaxial, Pin, Size 8, 75 Ohms
ARINC SPECIFICATION 600 – Page 210
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating.
Requirements:
Materials:
Body components
Insulator
Crimp ferrule
Center contact
Plating
Brass per QQ-B-626
TPFE per ASTM-D-1710
Brass per QQ-B-626
Beryllium copper per ASTM-B-196
Gold per AMS 2422, 50 microinches, minimum over 50 microinches
nickel underplate per QQ-N-290
Performances:
-65 °C to +125 °C.
75 Ω nominal
325 Vrms at sea level.
0 to 500 MHz
1.30:1
10 mΩ max (center)
1.5 mΩ max (outer body)
Insulation resistance 5000 MΩ min.
D.W.V
750 Vrms at sea level.
Tensile Strength
The size 8 contact below is similar to that described in
MIL-C-39029/59D. The user should refer to the guidance regarding
tensile strength provided in that document
Temperature range
Impedance
Rated voltage
Frequency range
V.S.W.R
Contact resistance
Tooling:
Insertion/Extraction Tool with M81969/29-01
Crimping Tool:
Center Contact
Outer Body
M22520/2-01 with locator recommended by the contact manufacturer
M22520/5-01 with die M22520/5-05
ARINC SPECIFICATION 600 – Page 211
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 14.
Figure 19-74.2 – Contacts, Electrical, Coaxial, Socket, Size 8, 75 Ohms
ARINC SPECIFICATION 600 – Page 212
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating.
Requirements:
Materials:
Body components
Insulators
Center Contact
Crimp ferrule
Plating
Copper alloy
PTFE per ASTM S-1710-99 or equivalent
Beryllium copper per ASTM-B-196
Or copper alloy
Copper alloy or brass per ASTM B-16
Gold per AMS 2422, 50 microinches minimum over 50
microinches minimum nickel underplate per QQ-N-290
Performance:
Temperature range
Impedance
Frequency range
VSWR
RF Insertion Loss
Rated voltage
Contact resistance
Insulation resistance
Dielectric withstanding voltage
Crimp Tensile Strength:
-65 °C to +125 °C
50 ohms nominal
0 – 500 MHz
1.30 : 1 maximum
0.3 dB maximum
325 Vrms at sea level
Center contact with 1.0 Amp test current
15 mΩ initial
30 mΩ after test
Outer body with 12.0 Amp test current
30 mΩ initial
45 mΩ after test
5,000 Megohms minimum
1,000 Vrms at sea level
The size 8 contact below is similar to that described in
MIL-C-39029/59D. The user should refer to the guidance
regarding tensile strength provided in that document
Crimp Tooling:
Center Contact
Outer Body
M22520/2-01 Tool with Locator
as recommended by the contact manufacturer
M22520/5-01 Tool with die set
as recommended by the contact manufacturer
ARINC SPECIFICATION 600 – Page 213
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 14.
Figure 19-75.1 – Contact Electrical, Pin, Crimp, Size 8, 50 Ohms
ARINC SPECIFICATION 600 – Page 214
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating.
Requirements:
Materials:
Body components
Insulators
Center Contact
Crimp ferrule
Plating:
Copper alloy
PTFE per ASTM S-1710-99 or equivalent
Beryllium copper per ASTM-B-196
Or copper alloy
Copper alloy or brass per ASTM B-16
Gold per AMS 2422, 50 microinches minimum over
50 microinches minimum nickel underplate per QQ-N-290
Performance:
Temperature range
Impedance
Frequency range
VSWR
RF Insertion Loss
Rated voltage
Contact resistance
Insulation resistance
Dielectric withstanding voltage
Crimp Tensile Strength
-65 °C to +125 °C
50 ohms nominal
0 – 500 MHz
1.30 : 1 maximum
0.3 dB maximum
325 Vrms at sea level
Center contact with 1.0 Amp test current
15 mΩ initial
30 mΩ after test
Outer body with 12.0 Amp test current
30 mΩ initial
45 mΩ after test
5,000 Megohms minimum
1,000 Vrms at sea level
The size 8 contact below is similar to that described in
MIL-C-39029/59D. the user should refer to the guidance
regarding tensile strength provided in that document
Crimp Tooling:
Center contact
Outer Body
M22520/2-01 Tool with Locator as recommended by the
contact manufacturer
M22520/5-01 Tool with die set as recommended by the
contact manufacturer
ARINC SPECIFICATION 600 – Page 215
ATTACHMENT 19
CONNECTOR SPECIFICATION
Drawing updated by Supplement 14.
Figure 19-75.2 – Contact, Electrical, Socket, Crimp, Size 8, 50 Ohms
ARINC SPECIFICATION 600 – Page 216
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating
Requirements:
Materials:
Body components
Insulators
Center Contact
Crimp ferrule
Plating
Copper alloy
PTFE per ASTM S-1710-99 or equivalent
Beryllium per copper per ASTM-B-196
or copper alloy
Copper alloy or brass per ASTM B-16
Gold per AMS 2422, 50 microinches minimum over
50 microinches minimum nickel underplate per QQ-N-290
Performance:
Temperature range
Rated voltage
Contact resistance
Insulation resistance
Dielectric withstanding voltage
Crimp Tensile Strength
-65 °C to +125 °C
325 Vrms at sea level
Center contact with 1.0 Amp test current
15 mΩ initial
30 mΩ after test
Outer contact with 12.0 Amp test current
30 mΩ initial
45 mΩ after test
5,000 Megohms minimum
1,000 Vrms at sea level
Center Contact5 lbs. minimum
Outer Contact15 lbs. minimum
Crimp Tooling:
Center Contact
Outer Contact
M22520/2-01 Tool with Locator as recommended by the
contact manufacturer
M22520/10-01 Tool with die set as recommended by the
contact manufacturer
Drawing updated by Supplement 14.
Figure 19-76.1 – Contact, Electrical, Shielded, Pin, Crimp, Size 12, 50 Ohms
ARINC SPECIFICATION 600 – Page 217
ATTACHMENT 19
CONNECTOR SPECIFICATION
Notes:
1. Unless otherwise specified, dimensions are in inches.
2. Dimensions shown apply after plating.
Requirements:
Materials:
Body components
Insulators
Center Contact
Crimp ferrule
Plating
Copper alloy
PTFE per ASTM S-1710-99 or equivalent
Beryllium copper per ASTM-B-196
or copper alloy
Copper alloy or brass per ASTM B-16
Gold per AMS 2422, 50 microinches minimum over
50 microinches minimum nickel underplate per QQ-N-290
Performance:
Temperature range
Rated voltage
Contact resistance
Insulation resistance
Dielectric withstanding voltage
Crimp Tensile Strength
-65 °C to +125 °C
325 Vrms at sea level
Center contact with 1.0 Amp test current
15 mΩ initial
30 mΩ after test
Outer body with 12.0 Amp test current
30 mΩ initial
45 mΩ after test
5,000 Megohms minimum
1,000 Vrms at sea level
Center contact5 lbs minimum
Outer Contact15 lbs minimum
Crimp Tooling:
Center Contact
Outer Contact
M22520/2-01 Tool with Locator as recommended by the
contact manufacturer
M22520/10-01 Tool with M22520/10-05A die set as
recommended by the contact manufacturer
Drawing updated by Supplement 14.
Figure 19-76.2 – Contact, Electrical, Shielded, Socket, Crimp, Size 12, 50 Ohms
ARINC SPECIFICATION 600 – Page 218
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
ATTACHMENT 20 CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS
SIZE 8 QUADRAX TYPE
This attachment describes details of one possible connector type that may be used
for Ethernet installation.
1.0
Dimensions and Mass
Dimensions and tolerances are given in millimeters (mm) and apply after surface
treatment.
The mass of the contact is 10 g maximum.
Center Contact (Pin) minimum length of constant diameter = 2.36 min
The notes of Appendix 4 apply to this contact assembly
Dimensions depend on cable size
2.0
Pin Component Definition
2.1
Rear Release/Rear Removeable Design
2.1.1
Pin Component Outer Body
Figure 20–2.1.1A shows the pin component layout.
Appendix 4 applies
All dimensions are in mm
Drawing updated by Supplement 14.
Figure 20-2.1.1A – Pin Component Outer Body #8 Quadrax
ARINC SPECIFICATION 600 – Page 219
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
Figure 20-2.1.1B shows the alignment boot for the pin component outer body.
Drawing updated by Supplement 14.
Figure 20-2.1.1.B – Alignment Boot
ARINC SPECIFICATION 600 – Page 220
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
Other dimensions should be compatible with the following crimping tools:
INNER CONTACTS
Crimping Tool
M22520/2-01
Die or Positioner
K709
OUTER CONTACT
M22520/5-01
M22520/5-45
All dimensions are in mm.
Drawing updated by Supplement 14.
Figure 20-2.1.2 – Pin Component Signal #24 Contact
ARINC SPECIFICATION 600 – Page 221
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
2.2
Front Release/Front Removeable Design
Appendix 4 applies
Drawing updated by Supplement 14.
Figure 20-2.2A – Front Release/Front Removable #8 Quadrax Contact
ARINC SPECIFICATION 600 – Page 222
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
Drawing updated by Supplement 14.
Figure 20-2.2B – Hole Positioning for Front Release/Front Removable #8 Quadrax Contact
ARINC SPECIFICATION 600 – Page 223
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
Socket Component Definition
3.1
Socket Outer Body
7.31 max 7.25 min
4.65 max 4.48 min
3.0
Dim X 6.0 in
Start of socket tine lead-in
Mates with 5.51-5.55 dia pin
8.0" Min.
Dim L
(Diameter of this area is 7.31/7.25) *
(Contact shoulder excluded)
* Does Not Apply To Hooded Contacts
.24 Min
Dim.
Appendix 4 applies
Figure 20-3.1 – Socket Outer Body #8 Quadrax
ARINC SPECIFICATION 600 – Page 224
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
3.2
Socket Component Signal Contact
All dimensions are in mm
Other dimensions should be compatible with the following crimping tools:
INNER CONTACTS
Crimping Tool
M22520/2-01
Die or Positioner
K709
OUTER CONTACTS
M22520/5-01
M22520/5-45
All dimensions are in mm
Drawing updated by Supplement 14.
Figure 20-3.2 – Socket Component Signal #24 Contact
ARINC SPECIFICATION 600 – Page 225
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
4.0
Contact Location inside ARINC 600 Connector
4.1
Pin Component in Shell
SIZE
A
B
C
22
9.91/9.30
/
2.16/1.80
20
9.45/8.18
0.68/0.33
/
16
13.13/11.89
0.68/0.33
/
12
13.05/12.04
0.68/0.33
/
8 QUADRAX
10.60/9.60
0.68/0.33
/
5 COAX
9.88/8.69
0.68/0.33
/
Figure 20-4.1 – Pin Component Shell
ARINC SPECIFICATION 600 – Page 226
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
4.2
Socket Component in Shell
Ø5.91 max
SIZE
D
E
F
22
4.70/3.68
/
2.97/2.56
20
2.51/1.45
0.48/0.13
/
16
3.20/2.16
0.48/0.13
/
12
3.15/2.18
0.48/0.13
/
8 QUADRAX
2.75/1.65
0.48/0.13
/
5 COAX
2.72/2.16
0.48/0.13
/
Figure 20-4.2 – Socket Component Shell
ARINC SPECIFICATION 600 – Page 227
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
5.0
Compatibility/Feasibility with Existing Connectors
ARINC 600
C
ARINC 404
C
EN 3545
C
NAS 1599
C
EN 2997
C
MIL 38999
F
SUB-D
N/A
Legend:
C: Compatible
F: Feasible with design adaptation
N/A: Not Applicable
6.0
ARINC 600 Insert Definition
Section 6.0 provides size 8 quadrax type contact locations inside various ARINC
600 connectors. For other contact cavities (size 5, 12, 16, 20, and 22), the location
should comply with requirements of the ARINC 600 specification.
6.1
6.1.1
Insert Layout I – Q11
Contact Style
Quantity
#8 Quadrax
11
Rear Release/Rear Removable Socket Contact
Figure 20–6.1.1 shows front mating face.
Ground continuity on all cavities.
2.00 Max
Drawing not to scale
All dimensions in mm
Figure 20-6.1.1 – Plug Front Mating Face
ARINC SPECIFICATION 600 – Page 228
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.1.2
Front Release/Front Removable Pin Contacts
Figure 20–6.1.2 shows receptacle front mating face.
Ground continuity on all cavities.
Drawing not to scale.
All dimensions in mm.
Figure 20-6.1.2 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 229
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.1.3
Rear Release/Rear Removable Pin Contacts
Figure 20–6.1.3 shows receptacle front mating face.
Grounding continuity on all cavities
2.00 Max
Drawing not to scale.
All dimensions in mm.
Figure 20-6.1.3 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 230
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.2
Insert Layout II – IIQ2
Contact Style
#8 Quadrax
#12
#16
#20
6.2.1
Quantity
2
4
3
4
Rear Release Rear Removable Socket Contacts
Figure 20–6.2.1 shows plug front mating face.
Grounding continuity on size 8 cavities
Drawing not to Scale
All dimensions in mm
Figure 20-6.2.1 – Plug Front Mating Face
ARINC SPECIFICATION 600 – Page 231
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.2.2
Front Release/Front Removable Pin Contacts
Figure 20–6.2.2 shows receptacle front mating face.
Grounding continuity on size 8 cavities
Drawing not to Scale
All dimensions in mm
Figure 20-6.2.2 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 232
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.2.3
Rear Release/Rear Removable Pin Contacts
Figure 20–6.2.3 shows receptacle front mating face.
Grounding continuity on size 8 cavities
Drawing not to Scale
All dimensions in mm
Figure 20-6.2.3 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 233
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.3
Insert Layout II – Q6
Contact Style
#8 Quadrax
6.3.1
Quantity
6
Rear Release/Rear Removable Socket Contacts
Figure 20–6.3.1 shows plug front mating face.
Ground continuity on all cavities
Drawing not to Scale
Figure 20-6.3.1 – Plug Front Mating Face
ARINC SPECIFICATION 600 – Page 234
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.2.3
Front Release/Front Removable Pin Contacts
Figure 20–6.3.2 shows receptacle front mating face.
Ground continuity on all cavities
Drawing not to Scale
Drawing updated by Supplement 14.
Figure 20-6.3.2 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 235
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.3.3
Rear Release/Rear Removable Pin Contacts
Figure 20-6.3.3 shows receptacle front mating face.
Ground continuity on all cavities.
Drawing not to Scale
Figure 20-6.3.3 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 236
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.4
Insert Layout II – 64Q2
6.4.1
Rear Release/Rear Removeable Contacts
Figure 20–6.4.1 shows plug front mating face.
Grounding continuity on size 8 cavities
Contact Style
#8 Quadrax Socket
#16 Socket
#22 Pin
Quantity
2
2
60
Drawing not to Scale
Figure 20-6.4.1 – Plug Front Mating Face
ARINC SPECIFICATION 600 – Page 237
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.4.2
Front Release/Front Removable Contacts
Figure 20–6.4.2 shows receptacle front mating face.
Grounding continuity on size 8 cavities
Contact Style
#8 Quadrax Pin
#16 Pin
#22 Socket
Quantity
2
2
60
Drawing not to Scale
Drawing updated by Supplement 14
Figure 20-6.4.2 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 238
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.4.3
Rear Release/Rear Removable Contacts
Figure 20–6.4.3 shows receptacle front mating face.
Ground continuity on size 8 cavities
Contact Style
#8 Quadrax Pin
#16 Pin
#22 Socket
Quantity
2
2
60
2.00 Max
Drawing not to Scale
Figure 20-6.4.3 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 239
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.5
Insert Layout III – 70Q2
6.5.1
Rear Release/Rear Removable Contacts
Figure 20–6.5.1 shows plug front mating face.
Grounding continuity on size 8 cavities
Contact Style
#8 Quadrax Socket
#22 Pin
Quantity
2
68
Drawing not to Scale
Figure 20-6.5.1 – Plug Front Mating Face
ARINC SPECIFICATION 600 – Page 240
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.5.2
Front Release/Front Removable Contracts
Figure 20–6.5.2 shows receptacle front mating face.
Grounding continuity on size 8 cavities
Contact Style
#8 Quadrax Pin
#22 Socket
Quantity
2
68
Drawing not to Scale
Drawing updated by Supplement 14.
Figure 20-6.5.2 – Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 241
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.5.3
Rear Release/Rear Removable Contacts
Figure 20–6.5.3 shows receptacle front mating face.
Ground continuity on size 8 cavities
Contact Style
#8 Quadrax Pin
#22 Socket
Quantity
2
68
11.43
8.89
6.35
3.81
1.27
3.8 MAX
8.89
3.81
1.27
8.64
2.00 Max
8.00
3 MAX
R 1.3 MAX
Drawing not to Scale
Figure 20-6.5.3 – Receptacle Front Mating Face
11.43
6.35
ARINC SPECIFICATION 600 – Page 242
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.5.4
Rear Release/Rear Removable Contacts
Figure 20-6.5.4 shows plug front mounting face.
Ground continuity on size 8 cavities.
Figure 20-6.5.4 does not show keying arrangements, but key on socket opening to
be 2.00 max.
Contact Style
#22 Pin
#8 Quadrax Socket
EXT
rear
rear
Quantity
118
2
Dimensions in mm
Figure 20-6.5.4 – Contact Arrangement 120Q2 Plug Front Mating Face
ARINC SPECIFICATION 600 – Page 243
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
6.5.5
Rear Release/Rear Removable Contacts
Figure 20-6.5.5 shows receptacle front mounting face.
Ground continuity on size 8 contacts.
Figure 20-6.5.5 does not show keying arrangements, but key on socket opening to
be 2.00 max.
Contact Style
#22 Socket
#8 Quadrax Pin
EXT
rear
rear
Quantity
118
2
Dimensions in mm
Note: A front contact release version of the insert is also available.
Drawing updated by Supplement 15.
Figure 20-6.5.5 – Contact Arrangement 120Q2 Receptacle Front Mating Face
ARINC SPECIFICATION 600 – Page 244
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
Drawing updated by Supplement 14.
Figure 20-6.6 – Keying Configuration
ARINC SPECIFICATION 600 – Page 245
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
7.0
Electrical Performance
7.1
Characteristic Impedance
Characteristic impedance is 100 ± 10 Ohms.
7.2
7.3
7.4
Maximum Attenuation
Frequency (MHz)
Maximum attenuation of contacts (dB)
1
4
10
16
20
31.25
62.50
100
0.01
0.03
0.03
0.03
0.03
0.04
0.10
0.30
Minimum Cross Talk (Next)
Frequency (MHz)
Minimum cross talk (dB)
1
4
10
16
20
31.25
62.5
100
65
65
60
56
54
50
44
40
Minimum Return Loss
Frequency (MHz)
>1.0
<20
>=20
<=100
7.5
Minimum return loss (dB)
23
23
14
14
Bonding and Electrical Continuity
After environmental testing, the quadrax shell should be bonded to the ARINC 600
connector shell with a maximum impedance equivalent to a series of 10 mΩ and an
inductance of 5 nH.
If Z is the complex impedance, f the frequency in Hz, and L the inductance in Henry,
that means:
| |
2 2
from DC to 100 MHz.
In addition, when a metallic insert is used, it should be bonded to the ARINC 600
connector shell with a maximum resistance of 5 mΩ.
ARINC SPECIFICATION 600 – Page 246
ATTACHMENT 20
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 QUADRAX TYPE
7.6
Transfer Impedance
[TBD]
8.0
Insertion/Extraction Tool
Drawing updated by Supplement 14.
Figure 20.6.7 – Typical Insertion/Extraction Tool
ARINC SPECIFICATION 600 – Page 247
ATTACHMENT 21
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 TWINAX TYPE
ATTACHMENT 21 CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS
SIZE 8 TWINAX TYPE
1.0
Introduction
This attachment provides interface details of #8 Twinax contact. Text and drawings
updated in Supplement 14.
2.0
Dimensions and Mass
Refer to Figures 21-1 through 21-4 of this attachment. Dimensions and tolerances
are given in inches.
2.1
Socket Contact Dimensions
Refer to Figures 21-1 and 21-2 for socket contact interface dimensions for a rear
release size #8 Twinax socket contact.
2.2
Pin Contact Dimensions
Refer to Figures 21-3 and 21-4 for pin contact interface dimensions for a front
release size #8 Twinax pin contact.
2.3
Mass
The mass of the contact is undefined.
ARINC SPECIFICATION 600 – Page 248
ATTACHMENT 21
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 TWINAX TYPE
TO END OF INTERMEDIATE PIN CONTACT AND
CONTER SOCKET INSULATOR
TO END OF OUTER SOCKET CONTACT
TO END OF CENTER SOCKET CONTACT
Figure 21-1 – Typical Size 8 Twinax Socket Interface Dimensions for ARINC 600 Connector
Drawing updated by Supplement 14
Figure 21-2 – Center Socket and Intermediate Contact Subassembly Dimensions
ARINC SPECIFICATION 600 – Page 249
ATTACHMENT 21
CONNECTOR ELECTRICAL AND MECHANICAL CHARACTERISTICS SIZE 8 TWINAX TYPE
Figure 21-3 – Typical Size 8 Twinax Pin Interface Dimensions for ARINC 600 Connector
Drawing updated by Supplement 14
Figure 21-4 – Center Pin and Intermediate Contact Subassembly Dimensions
ARINC SPECIFICATION 600 – Page 250
APPENDIX 1
NOT USED
APPENDIX 1
NOT USED
THIS APPENDIX DELETED BY SUPPLEMENT 19
ARINC SPECIFICATION 600 – Page 251
APPENDIX 2
ENVIRONMENTAL REQUIREMENTS FOR MILITARY APPLICATIONS
APPENDIX 2
ENVIRONMENTAL REQUIREMENTS FOR MILITARY APPLICATIONS
*This appendix was added to ARINC Specification 600 by Supplement 4.
The United States military services, and, no doubt, those of other countries too, are
seeking ways to use off-the-shelf commercial avionics wherever possible because
of the obvious economic benefit. The ARINC 700-Series commercial avionics can
be used in most transport aircraft application. However, in some military applications
this benefit may only be realized if the equipment can tolerate a more severe
operating environment than that found in commercial transport aircraft. This
Appendix details the differences between these environments that an equipment
manufacturer contemplating serving both markets with a single unit should consider
during design work. He should be aware, of course, that the commercial users will
not find his product desirable if meeting the more stringent military requirements
produce significant cost, weight, or other penalties. They will be interested; however,
if a mutual benefit can be demonstrated.
The content of this Appendix is presented with reference to certain sections in
ARINC Specification 600. The section numbers follow the subject titles in
parentheses.
Vibration, Shock, and Acceleration (See Section 3.1.2)
In addition to the requirements stated in Attachment 13 to ARINC Specification 600
concerning vibration, the equipment design shall be shown to be adequate to
survive and operate in the service environment and to withstand transportation,
handling, and servicing. One of the following demonstration methods should be
used:
a. A combination of dynamic analyses, shock and random vibration testing, and
service experience.
b. A random vibration test without the use of vibration isolation devices. Test
levels shall be 0.04 g²/Hz from 20 to 1000 Hz with a duration of one hour in
each of 3 orthogonal axes. Note that this is a general ruggedness test and
not a direct representation of flight environment.
Cooling (See Section 3.1.3)
The requirements of this section shall apply except that precluding the use of
surface openings on equipment not requiring forced air cooling. Such openings are
permitted on any surface (except the bottom surface) at the discretion of the
equipment designer. Also, equipment designers should note that in some military
applications the aircraft may be operated unpressurized at altitudes up to 25,000
feet. Military users accept that this will reduce the cooling air available and may
have a deleterious effect on equipment reliability.
Power Dissipation (See Section 3.1.3.2)
The power dissipated within the LRU shall be selected by the equipment designer
but shall in no case exceed the value shown in Attachment 12 to ARINC
Specification 600 for the equipment case size. Level 1 cooling-air pressure drop
(5 mm water gauge) is preferred and shall be used wherever possible.
ARINC SPECIFICATION 600 – Page 252
APPENDIX 2
ENVIRONMENTAL REQUIREMENTS FOR MILITARY APPLICATIONS
The Equipment Rack (See Section 3.2)
The requirements of this section shall apply except for the requirement (in Section
3.2.5.2) to collect exhaust cooling air from each shelf on a rack. While such
provisions are not excluded, military installations may dump exhaust cooling air
directly into the equipment bay.
Electrical Bonding Interface (See Section 3.2.4)
In addition to the requirements stated in Section 3.2.4 of ARINC 600, the
requirements of MIL-B-5087, Sections 3.3.2 and 3.3.5.1, shall apply (prior to
March 18, 1997). After March 18, 1997, the requirements of MIL-STD-464 apply.
Thermal Design Conditions (See Section 3.5.1.6)
This requirement applies except for subsection (g), which is changed as follows:
“Coolant air flow rate of 165 kilograms per hour per kilowatt based on actual heat
dissipation at condition (b) above.
COMMENTARY
The lower coolant flow is specified in recognition of the situation in
which 220 kilograms per hour per kilowatt air flow available in a civil
configuration requires redistribution among the mission-related
avionics for military use and it is not feasible to increase the capacity
of the aircraft environmental control system.”
Coolant Air Flow Rate (See Section 3.5.4.3)
This requirement applies except that the design air-flow rate shall be 165 kilograms
per hour per kilowatt at sea level (inlet temperature 40 °C). This air flow shall be
reduced to 102 kilograms per hour per kilowatt when an inlet temperature of 30 °C
is supplied by the aircraft environmental control systems.
Thermal Interface Information (See Section 3.5.7)
The flow rates stated in Section 3.5.7, subsection (c), shall be the same as the rates
in Sections 3.5.1.6 and 3.5.4.3 stated above.
Power Quality (See Section 3.6.1)
The requirements of MIL-STD-704C shall govern power quality.
Severe Humidity Environment (RTCA DO-160, Section 6.0)
Because of the deployment conditions encountered by military aircraft, all avionics
equipment shall be qualified (i.e., tested) for Category B, Level I humidity
environment.
Temperature/Altitude Tests (RTCA DO-160, Section 4.0)
Avionics equipment for general military use shall withstand the condition stated for
Category E1 for temperature/altitude, except for high operating temperatures.
High Operating Temperature (RTCA DO-160, Section 4.0)
The high operating temperatures of Category B1 shall apply.
Note: This sample instruction set is for information only. Assembly
instructions should be delivered to the customer with the
product.
ARINC SPECIFICATION 600 – Page 253
APPENDIX 3
TYPICAL ASSEMBLY INSTRUCTIONS, SIZE 1 RF CONTACT
APPENDIX 3
TYPICAL ASSEMBLY INSTRUCTIONS, SIZE 1 RF CONTACT
ARINC SPECIFICATION 600 – Page 254
APPENDIX 3
TYPICAL ASSEMBLY INSTRUCTIONS, SIZE 1 RF CONTACT
ARINC SPECIFICATION 600 – Page 255
APPENDIX 3
TYPICAL ASSEMBLY INSTRUCTIONS, SIZE 1 RF CONTACT
ARINC SPECIFICATION 600 – Page 256
APPENDIX 4
GUIDELINES FOR AVIONICS 10/100BASE-T ETHERNET CONNECTOR CHARACTERISTICS SIZE 8 QUADRAX
TYPE
APPENDIX 4
GUIDELINES FOR AVIONICS 10/100BASE-T ETHERNET CONNECTOR
CHARACTERISTICS SIZE 8 QUADRAX TYPE
Table A4-1 Qualification Test Parameters for Ethernet Connector Pins
Notes: Unless otherwise specified, dimensions are in mm.
Dimensions apply after plating.
Text and tables updated by Supplement 14.
Requirements:
Materials:
Outer body:
Center contact:
Crimp ferrule:
Insulator:
Plating:
Copper alloy
Copper alloy
Copper alloy
PTFE per ASTM-D-1710 or other suitable material
Gold per AMS2422, 1.27 micrometer minimum over a 1.27
micrometer under-plate per QQ-N-290
Performances:
-65 °C to + 200 °C
center conductor = 45N min.
Shield = 110N min.
Gauge insertion and extraction force:
Insertions force from center contact: 1.65N max.
Extractions force from center contact: 0.25N min.
Insertions force from outer-body: 8N max.
Extraction force from outer body: initial = 1.2N min.
After test = 0.8N min.
Center contact max. pin gage = 0.648 0/-0.0025
Center contact min. pin gage = 0.622 0/+0.0025
Outer body max. pin gage = 5.563 0/-0.005
Outer body min. pin gage = 5.512 0/+0.005
Insulation resistance:
Measured between signal contacts and between signal contacts and
outer-body:
≥ 5000 MΩ at ambient temperature
≥ 1000 MΩ at 200 °C
Dielectric Withstanding Voltage:
Sea level:
≥1000 Vrms between signal contacts
≥ 500 Vrms between signal contacts and outer-body
70000 feet:
≥ 125 Vrms between signal contacts
≥ 125 Vrms between signal contacts and outer-body
Contact resistance low level:
Signal contacts:
15 mΩ initial
30 mΩ after test
Temperature range:
Crimp tensile strength:
ARINC SPECIFICATION 600 – Page 257
APPENDIX 4
GUIDELINES FOR AVIONICS 10/100BASE-T ETHERNET CONNECTOR CHARACTERISTICS SIZE 8 QUADRAX
TYPE
Contact resistance at rated current: rated current = 1A for center contacts and 12A for outerbody
Center contacts:
15 mΩ initial
30 mΩ after test
Outer-body:
3 mΩ initial
4 mΩ after test
Characteristic impedance:
100 Ω nominal
Return loss:
Should meet Attachment 20, Section 7.4 when measured according
to IEC60603-7 Amd1/ISO11801 or equivalent
Transfer impedance:
Should meet the requirements of Attachment 20, Section 7.6 when
measured according to EN2591-212 or equivalent
Attenuation:
Should meet the requirements of Attachment 20, Section 7.2 when
measured according to IEC60603-7 Amd1/ISO11801 or equivalent
Cross talk:
Should meet the requirements of Attachment 20, Section 7.3 when
measured according to IEC60603-7 Amd1/ISO11801 or equivalent
Bonding and electrical continuity: See Attachment 20, Section 7.5
Table A4-2 – Maximum Attenuation of the Contacts at 25 °C
Frequency (MHz)
1
4
10
16
20
31.25
62.50
100
Maximum attenuation of the contacts (dB)
0.01
0.03
0.03
0.03
0.03
0.04
0.10
0.30
The maximum attenuation should be adjusted for elevated temperature (see Quad
cable)
Table A4-3 – Minimum Near End Crosstalk Loss of the Contacts
Frequency (MHz)
Next contacts (dB)
1
4
10
16
20
31.25
62.50
100
65
65
60
56
54
50
44
40
ARINC SPECIFICATION 600 – Page 258
APPENDIX 4
GUIDELINES FOR AVIONICS 10/100BASE-T ETHERNET CONNECTOR CHARACTERISTICS SIZE 8 QUADRAX
TYPE
Table A4-4 – Transfer Impedance
Frequency (MHz)
dc
0.1
1
5
10
20
50
100
Maximum Transfer impedance (Zt max)
(m/m)
20
20
20
20
30
45
100
200
Text and tables updated by Supplement 14.
ARINC SPECIFICATION 600 – Page 259
APPENDIX 5
ETHERNET CONTACT CONSIDERATIONS FOR NEW DESIGNS
APPENDIX 5
1.0
ETHERNET CONTACT CONSIDERATIONS FOR NEW DESIGNS
Introduction
Note: Appendix 5 added by Supplement 14 to ARINC
Specification 600.
At the AEEC General Session held in October 2002, AEEC discussed the
recommendation of the New Installation Concepts (NIC) Subcommittee to include
three types of contacts compatible with 100BaseT Ethernet in ARINC
Specification 600. The NIC Subcommittee recommendation provided for a choice of
Ethernet contacts for avionics connectors in future ARINC Characteristics. AEEC
recognized that the multiple choice of contacts could reduce the potential for
interchangeability of avionics. AEEC indicated that subcommittees and working
groups developing new standards using 100BaseT Ethernet interfaces will ultimately
have the responsibility of choosing the best contact for the application. AEEC stated
that the choice should maximize commonality.
AEEC had discussed the possibility of specifying a contact in ARINC Specification
600 that would be the “preferred contact” for use with 100BaseT Ethernet
applications. However, they recognized that performance requirements, space and
weight limitations, and environment will ultimately affect the choice of the contact
that is optimal for the conditions. Therefore, no preference was recommended. As
an alternative, AEEC suggested that pertinent material discussed during previous
NIC Subcommittee meetings be used to create this appendix comprising
background and guidance material for use by future subcommittees and working
groups in their standardization activities. AEEC stated that adapters and other
methods to minimize the effect of using different types of contacts on an airplane
should be provided in the guidance material.
2.0
Background
2.1
Contact Candidates Identified
The Aircraft Data Network (ADN) Working Group was chartered originally by AEEC
to develop an onboard data network standard based on commercial standards. The
ADN Working Group prepared multiple parts to ARINC Specification 664 addressing
the Aircraft Data Network according to AEEC guidance. Part 2 of ARINC 664
addressed Ethernet physical and data link layers. As a part of this effort, the ADN
Working Group and the Connector Working Group developed specifications for a
connector contact deemed suitable for aircraft applications employing a bus speed
of 100 Mbps.
After a considerable amount of work had been accomplished in developing a
connector standard (Quadrax), Boeing introduced an additional candidate for the
standard. Their contribution was a concentric Twinax contact that had been used on
some Boeing airplanes. In response, the ADN Working Group, in collaboration with
the Connector Working Group, developed definitions for both types of contacts.
AEEC, at their 2001 Special Session, directed that the physical definition for this
connector contact be incorporated into ARINC Specification 600, rather than
ARINC 664, and that the work on Ethernet contacts should be assumed by the NIC
Subcommittee. The AEEC instructed the NIC Subcommittee to review these
contacts and to pick the best single approach for a common standard. Advocates for
a single standard contact in ARINC Specification 600 suggested that a single
ARINC SPECIFICATION 600 – Page 260
APPENDIX 5
ETHERNET CONTACT CONSIDERATIONS FOR NEW DESIGNS
standard would provide a better opportunity for interchangeability and commonality
across airplanes employing 100BaseT Ethernet systems. The AMC Steering Group
also supported a single standard.
2.2
NIC Subcommittee Recommendation
At the NIC Subcommittee meeting held primarily to address these contacts,
representatives from several companies summarized their activities related to the
use of size 22, Twinax and Quadrax contacts and cables for Ethernet installations.
The presenters provided a rather compelling case to allow for freedom of choice
whereby any AEEC Subcommittee defining an LRU could choose the connector and
contacts best suited for the application. The equipment manufacturers did not state
a specific preference for any one connector contact or cable. They stated that they
would use the connector and contact specified either by a standard or a contract.
The airlines at the meeting were concerned that none of the presentations
supported a single standard contact.
The NIC Subcommittee, after much consideration, recommended that size 22 pins,
Twinax contacts, and Quadrax contacts be included in ARINC Specification 600 in
recognition that these approaches have already been implemented and that current
ARINC Standards refer to these types of contacts. However, the NIC Subcommittee
suggested that a letter be prepared and circulated to the airlines to obtain their
reaction and guidance regarding the NIC Subcommittee’s recommendation to
include all contact definitions in ARINC Specification 600.
2.3
Consequences of Multiple Contacts
The NIC Subcommittee recommendation to include multiple contact (and cable)
definitions in ARINC Specification 600 will allow system implementers to choose
different physical interfaces for the "backbone" data distribution systems onboard
airplanes. ARINC Subcommittees and Working Groups will then be faced with the
dilemma of choosing connector contacts for avionics boxes intended for installation
on airplanes that could employ different physical network standards. In this situation,
direct interchangeability of an avionics unit could be precluded between aircraft
types employing different physical system standards. The airlines will be placed in a
situation whereby units with identical functions may not be interchangeable as a
result of incompatible connectors. Further complicating the situation will be the need
for airlines to have spares for multiple types of contacts, and to provide tooling and
training for maintenance of different types of contacts and inserts.
3.0
Mitigation of Issues Involving Dissimilar Interfaces
The NIC Subcommittee had explored some potential solutions to resolving the
problem of connecting an avionics unit with one type of contact to an aircraft system
with a different physical standard. These techniques are addressed in the following
sections. However, it is recognized that these potential solutions are not ideal and
should be verified for viability prior to using them as part of a system design. Ideally,
it is better to specify systems with compatible electrical connections.
3.1
The “Y” Cable
The use of a “Y” cable between the two connectors has been identified as one
viable approach. With this technique, the two ends on the “Y” are connected to
Twinax contacts. The single end of the “Y” is connected to Quadrax contacts. The
point at which two cables become one, or one cable becomes two, should be near
ARINC SPECIFICATION 600 – Page 261
APPENDIX 5
ETHERNET CONTACT CONSIDERATIONS FOR NEW DESIGNS
the termination point at either end of the cable. This approach may not be effective
for long cable runs approaching 100 meters due to losses from the splices.
3.2
The Double Cable
A special double cable has been identified to allow for termination with either two
Twinax contacts or a single Quadrax contact. When the termination is a Quadrax
contact, both wires are run directly into the contact and the appropriate connections
are made inside the contact shell. One avionics manufacturer’s tests had indicated
that this technique should work in most applications. The losses that result from
using this approach need to be considered carefully in aircraft applications using
long cable runs.
3.3
Replication of Contacts
An alternative to the "cable patches" addressed above is the use of additional
contacts on avionics that accommodate each type of physical approach. However,
the airlines have indicated that using both types of contacts on a single avionics unit
is undesirable.
The NIC Subcommittee also considered an approach that could be implemented in
the design phase of new airplanes, particularly when an airplane uses one physical
standard for the “backbone” of the data communication system. An airplane with an
extensive onboard Ethernet system will require numerous units to function as
Ethernet switches for system interconnections and routing. One or more of those
units could include physical interfaces that allow for connection of avionics with
different physical contacts. For example, an airplane with a Quadrax-based Ethernet
system could employ Ethernet switches that provide a minimal number of Twinax
contacts for future expansion.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 1
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: August 1, 1978
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
May 4, 1978
SUPPLEMENT 1 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces changes into Specification 600 considered necessary to
improve the operational effectiveness of the system it describes.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod-colored paper, is the
Supplement itself. It contains descriptions of the changes introduced into the
Specification and, where appropriate, extracts from the original text for comparison
purposes. The second part consists of replacement white pages for the
Specification, modified as required by the Supplement. The modified and added
material on each replacement page is identified in the margin by a “c-1” indicator.
Existing copies of Specification 600 may be updated by simply inserting the
replacement white pages where necessary and destroying the pages they displace.
The goldenrod colored Supplement should be inserted inside the rear cover of the
Specification.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change and, for other than only very minor revisions, any text originally contained in
the Specification is reproduced for reference. For those changes that are either too
complex to be readily described or involve extensive revisions to attachments, the
original page appears in this section marked OBSOLETE – DO NOT USE. A
replacement white page for each of these pages is included in the second part of this
document, as noted in B above. In this way an accurate record of the development
of the Specification is preserved.
1.4.7 Standard International (S.I.) Units
DELETED reference to Appendix 3.
ADDED discussion on the term weight in the Commentary.
3.1.1.1
LRU Hold-Downs
REVISED the wording under this section and COMMENTARY Item 5.
3.1.1.2
Rear Panel
REVISED the wording under this section.
ADDED COMMENTARY
3.1.1.4
Maximum Weight
REVISED all references of mass in this section to weight.
3.1.1.5
Mating Force
ADDED lbs. reference.
3.1.2
Cooling
ADDED last sentence reference to Attachment 12.
SUPPLEMENT 1 TO ARINC SPECIFICATION 600 – Page b
3.1.3.1 Cooling Air Interface
REVISED the wording of third paragraph.
3.1.3.2
Power Dissipation
REVISED the wording of this section to call out two levels of pressure drop.
3.2.3.2
Front Retainer
REVISED the wording of this section and added references to insert or/extractor
forces.
3.2.3.2.1 LRU Hold-Down Details
ADDED this new section with commentary.
3.2.3.2.2 LRU Extractor Details
ADDED this new section.
3.2.4
Electrical Bonding Interface
DELETE “Design guidance is given in Appendix 1.”
3.3.2
Connector Mechanical Consideration
REVISED mms to mm (one place)
3.3.2.1
ADDED lbs. reference to S.I. units.
3.3.2.2
ADDED lbs. reference to S.I. units.
3.5.4.4
Coolant Air Quality
ADDED ISO unit reference.
3.5.4.5
Coolant Pressure Drop through the Equipment – Level 1 + Level 2
REVISED wording of this section to call out two levels of pressure drop and add
words and commentary on use of internal blowers.
COMMENTARY
For contamination sensitive units where indirect cooling is a must a
higher pressure drop may be required. Under such conditions, the
excess pressure drop must be offset internally. An internal fan may be
used for this purpose. It cannot be assumed that the rack can be
modified to provide sufficient flow to a unit with excessive pressure
drop.
3.5.4.6
Coolant Air Leakage from the Equipment
REVISED “shall” to “should”
3.5.5
Equipment Sidewall Temperature
REVISED “shall” to “should” (two places).
3.5.6
LRU Thermal Appraisal
REVISED wording of this section.
SUPPLEMENT 1 TO ARINC SPECIFICATION 600 – Page c
3.5.6.1
Identification and Data Tabulation for Heat Dissipating and Temperature
Critical Parts
REVISED wording of this section.
REVISED “shall” to “should” (11 places):
ATTACHMENT 2 – STANDARD LRU CASE SIZE
ATTACHMENT 3 – LOCATION OF CONNECTOR
ATTACHMENT 4 – MAXIMUM LRU MASS
ATTACHMENT 5 – RACK/SHELF DATUMS
ATTACHMENT 7 – RACK/LRU HOLD DOWN MECHANISMS
ATTACHMENT 8 – LRU GUIDE DIMENSIONS
ATTACHMENT 9 – COOLING APERTURES
ATTACHMENT 10 – CONNECTOR FORM FACTOR
ATTACHMENT 11 – CONTACT POSITION IDENTIFICATION and INSERT SIZE
ATTACHMENT 13 – ENVIRONMENTAL CONDITIONS FOR ELECTRICAL/ELECTRONIC
EQUIPMENT INSTALLED IN CONTROLLED TEMPERATURE AND PRESSURIZED
LOCATIONS
ATTACHMENT 17 – CONNECTOR ENGAGING POSITION
REVISED
ATTACHMENT 15 – MCU BACKPLATE CONNECTOR CUTOUT
ATTACHMENT 16 – RACK OR TRAY BACKPLATE CONNECTOR CUTOUT
DELETED
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 2
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: November 15, 1979
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
August 30, 1979
SUPPLEMENT 2 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces changes into Specification 600 considered necessary to
improve the operational effectiveness of the system it describes.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod-colored paper, is the
Supplement itself. It contains descriptions of the changes introduced into the
Specification and, where appropriate, extracts from the original text for comparison
purposes. The second part consists of replacement white pages for the
Specification, modified as required by the Supplement. The modified and added
material on each replacement page is identified in the margin by a “c-2” indicator.
Existing copies of Specification 600 may be updated by simply inserting the
replacement white pages where necessary and destroying the pages they displace.
The goldenrod-colored Supplement should be inserted inside the rear cover of the
Specification.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change and, for other than only very minor revisions, any text originally contained in
the Specification is reproduced for reference. For those changes that are either too
complex to be readily described or involve extensive revisions to attachments, the
original page appears in this section marked OBSOLETE- DO NOT USE. A
replacement white page for each of these pages is included in the second part of this
document, as noted in B above. In this way an accurate record of the development
of the Specification is preserved.
3.3.1.2
DELETED this paragraph along with “COMMENTARY” inasmuch as this material is
incorrect and inapplicable.
3.5.4.5
Coolant Air Pressure Drop Through the Equipment
REVISED third line to read - 250 ± 50 Pa
REVISED last two lines to read - Section 14.4 Step 5
ATTACHMENT 2 – STANDARD LRU CASE SIZE
Figure 2 - Optional Front Face Forward Projections
REVISED the front face forward projection dimension from 50.0 mm (1.97 in.) to now
read 63.5 (2.50).
ATTACHMENT 18 – INDEX PIN CODING
REVISED this Attachment to show updated views of connector shells and added
notes.
ATTACHMENT 19 – CONNECTOR DEVELOPMENT SPECIFICATION
REVISED this Attachment to provide the updated version of Boeing Specification
Control Drawing 10-61953 Revision “E” to incorporate the refinements in the
connector design that resulted from the Boeing test program.
SUPPLEMENT 2 TO ARINC SPECIFICATION 600 – Page b
ATTACHMENT 20 – RESULTS OF DESIGN VERIFICATION TEST PROGRAM FOR
ARINC 600 LOW INSERTION FORCE CONNECTORS
ADDED this Attachment which provides background information and the Abstract
from Boeing Document T6-6294 which describes Boeing test program on the ARINC
600 low insertion force (LIF) connector design.
Note: The complete Boeing Document T6-6294 has been published as Annex 1 to
ARINC 600 and is available separately as shown in the ARINC Document List.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 3
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: April 15, 1981
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
March 11, 1981
SUPPLEMENT 3 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces changes into Specification 600 considered necessary to
improve the operational effectiveness of the system it describes.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod-colored paper, is the
Supplement itself. It contains descriptions of the changes introduced into the
Specification and, where appropriate, extracts from the original text for comparison
purposes. The second part consists of replacement white pages for the
Specification, modified as required by the Supplement. The modified and added
material on each replacement page is identified in the margin by a “c-3” indicator.
Existing copies of Specification 600 may be updated by simply inserting the
replacement white pages where necessary and destroying the pages they displace.
The goldenrod-colored Supplement should be inserted inside the rear cover of the
Specification.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change and, for other than only very minor revisions, any text originally contained in
the Specification is reproduced for reference. For those changes that are either too
complex to be readily described or involve extensive revisions to attachments, the
original page appears in this section marked OBSOLETE- DO NOT USE. A
replacement white page for each of these pages is included in the second part of this
document, as noted in B above. In this way an accurate record of the development
of the Specification is preserved.
Section 3.3.2.4
ADDED “COMMENTARY” following this Section.
ATTACHMENT 7 – RACK/LRU HOLD DOWN MECHANISMS
REVISED this attachment to correct NAS 622 Hook dimension to 11.73 +.50 -.00
mm (was 10.82 +.50 -.00 mm).
ATTACHMENT 19 – CONNECTOR DEVELOPMENT SPECIFICATION
REVISED this Attachment to incorporate Revision “G” of Boeing Connector
Specification Control Drawing SCD-61953.
DELETED reference to Annex 1 to ARINC 600.
ATTACHMENT 20 – RESULTS OF DESIGN VERIFICATION TEST PROGRAM FOR
ARINC 600 LOW INSERTION FORCE CONNECTORS
Paragraph “D” added. References to Annex 1 to ARINC 600 deleted and replaced
with instructions on how to obtain copies of the documents originally planned to
constitute Annex 1.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 4
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: February 8, 1982
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
December 10, 1981
SUPPLEMENT 4 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement adds Appendix 2 to Specification 600. Appendix 2 describes the
environmental conditions expected by the United States Air Force on aircraft in
which they plan to use commercial avionics equipment designed for civil transport
aircraft.
B. ORGANIZATION OF THIS SUPPLEMENT
Replacement and additional white pages for Specification 600 are attached to this
buff-colored Supplement page. These white pages contain Appendix 2 and should
be incorporated into the Specification at the page number locations indicated. This
buff-colored page should be inserted into the Specification following Supplement 3.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change and, for other than only very minor revisions, any text originally contained in
the Specification is reproduced for reference. For those changes that are either too
complex to be readily described or involve extensive revisions to attachments, the
original page appears in this section marked OBSOLETE- DO NOT USE. A
replacement white page for each of these pages is included in the second part of this
document, as noted in B above. In this way an accurate record of the development
of the Specification is preserved.
ADDED
APPENDIX 2 - ENVIRONMENTAL REQUIREMENTS FOR MILITARY APPLICATIONS
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 5
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: August 12, 1983
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
November 2, 1982
SUPPLEMENT 5 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces a number of changes which improve the clarity and
correctness of the Specification 600.
Briefly these are:








Clarification of NIC Phases
Improved thermal appraisal
Added guidance on installing spare contacts
Added caution on use of NAS 622 Type E hooks
Changed environmental test categories
Updated connector specifications
Reorganized Attachment 19
Clarified LRU and shelf design forces.
B. ORGANIZATION OF THIS SUPPLEMENT
In view of the extensive reorganization and numerous minor changes, Supplement 5
will not be issued with replacement pages to update existing documents. Thus, a
completely updated ARINC 600-5 is available. The modified and added material is
identified with “c-5” symbols in the margins.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this supplement. Each change or addition is identified
using the Section number and title currently employed or the Section number and
title that will be employed when the Supplement is eventually incorporated. In each
case there is included a brief description of the addition or change.
1.2
SCOPE
Third sentence of paragraph 1.2 (a) commentary revised.
COMMENTARY to paragraph 1.2 (b) revised.
ADDED new note at end of Section 1.2.
3.1.1.1
LRU Hold-Downs
ADDED note to Section 3.1.1.1.
3.1.1.7
MCU Backplate Deflection
ADDED new Section 3.1.1.7.
3.2.3.1.2
Rack Backplate Deflection
Changed title and wording of 3.2.3.1.2.
3.2.3.2.1
LRU Hold-Down Details
ADDED note to Section 3.2.3.2.1.
3.3
The Rack and Panel Connector
Revised the paragraph and Commentary near the end of this section.
3.3.2 Connector Mechanical Considerations
ADDED new section 3.3.2.11 and Commentary which addresses installation of
contacts in unused contact cavities.
SUPPLEMENT 5 TO ARINC SPECIFICATION 600 – Page b
3.3.2.3
(No Title) (and numerous subsequent sections).
Changed reference to Attachment 19 (was Attachment 10).
3.3.5.1.1 Connector Position
Reworded last paragraph.
3.3.5.2.1 Backplate Connector Position
ADDED note relating to the use of shell size 1 side mounting provisions.
3.5.6.2
Thermal Evaluation Test
REVISED second and third paragraphs.
ADDED new sentence to existing Commentary.
3.6.1
Power Quality
Changed reference to RTCA and EUROCAE to call out current versions.
ATTACHMENT 10 – CONNECTOR FORM FACTOR
DELETED Attachment 10 in its entirety.
(For archival purposes see a copy of ARINC 600-4.)
ATTACHMENT 13 – ENVIRONMENTAL CONDITIONS FOR ELECTRICAL/ELECTRONIC
EQUIPMENT INSTALLED IN CONTROLLED TEMPERATURE AND PRESSURIZED
LOCATIONS
Revised the “connector” column to reference Attachment 19 (was Boeing SCD 1061953).
Changed the high temperature test category from “A-1” to “A-2”.
Changed reference to DO-160A (was D0-160).
14.2.1 Test Chamber and Airplane Mounting Simulation
REVISED last sentence of 14.2.1.
DELETED commentary to 14.2.1.
14.2.2.3 Measurements for Cooling Evaluation Test
Changed title of 14.2.2.3
Changed reference “14.3.2.2” to “14.2.2.4”
14.4
Test Procedures
Changed title of 14.4.
REVISED entire section 14.4.
TABLE 14-1
This table was revised in the following manner:




The units of M1 were changed from
to kg/hr/kw.
P3 was changed to P3
P3 for normal Ground Operation was changed from “20” to “30” to “See
3.5.4.5”
T8 for high temperature startup was changed from being undefined to
“operate at the same Q2 power which was required in Step (5) to maintain T8
at 60ºC “
SUPPLEMENT 5 TO ARINC SPECIFICATION 600 – Page c


T8 for Severe Continuous Operation was changed from “Within ± 2ºC of test
unit sidewall” to “75ºC”
General notes (g) and (h) were added
FIGURE 14-1 Standard Test Chamber
DELETED the words “INLET” and “EXHAUST”
FIGURE 14-1 Flag Notes
Replaced last two sentences of 2nd paragraph of Flag Note 1.
Deleted words “or ARINC 404A” from 1st paragraph of Flag Note 2.
Replaced 2nd paragraph of Flag Note 2
Replaced 3rd paragraph of Flag Note 2
Replaced last two (2) sentences of 4th paragraph of Flag Note 2.
FIGURE 14-2b. Airflow Schematic, showing ARINC 600 Test Chamber Reconnected
to perform an ARINC 404A Type “A” Cooling Test (Draw-Through)
REVISED title of FIGURE 14-2b. Labeled Duct B “BYPASS EXHAUST” with arrow to
indicate downward airflow.
FIGURE 14-2c. Airflow Schematic, showing an ARINC 600 Test Chamber
Reconnected to perform an ARINC 404A Type “B” Cooling Text (Natural Convection)
REVISED title of FIGURE 14-2c
FIGURE 14-3 Instrumentation Schematic, Test Chamber
ADDED the following to Figure 14-3




T9* at Duct C
T6* at Duct B
T2* at Duct A
to T3 on side view
Changed asterisk (*) definition from “ARINC 404A TYPE ‘A’ Cooling only (Downward
airflow)”
ATTACHMENTS 15 and 16 Connector Cutouts
Moved drawings from Attachment 19.
ATTACHMENT 19 - CONNECTOR SPECIFICATION
REVISED completely - Due to extensive text, see copy of ARINC 600-4 for archival
purposes.
APPENDIX 1 - BIBLIOGRAPHY OF THE AEEC ARINC 600 NEW INSTALLATION
CONCEPT (NIC)
ADDED AEEC letters published since August 1977.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 6
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: November 28, 1983
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
October 13, 1983
SUPPLEMENT 6 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement redefines connector foot-to-shell and connector content (datum K
to lower edge) dimensions and adds text clarifying the users’ desires concerning
connector engage and disengage forces. Additionally, the Supplement corrects a
number of errors discovered since the publication of Supplement 5.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod-colored paper, is the
Supplement itself. It contains descriptions of the changes introduced into the
Specification and, where appropriate, extracts from the original text for comparison
purposes. The second part consists of replacement white pages for the
Specification, modified as required by the Supplement. The modified and added
material on each replacement page is identified in the margin by a “c-6” indicator.
Existing copies of Specification 600 may be updated by simply inserting the
replacement white pages where necessary and destroying the pages they displace.
The goldenrod-colored Supplement should be inserted inside the rear cover of the
Specification.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change. A replacement white page for each of these pages is included in the second
part of this document, as noted in B above. In this way an accurate record of the
development of the Specification is preserved.
3.3.2.4
Engage and Disengage Forces
3.3.2.4.1 Future Designs
Text from Section 3.3.2.4 of Specification 600-5 transferred to this sub-section.
Commentary amended to delete reference to Attachment 19.
3.3.2.4.2 Existing Designs
New section added by this Supplement.
ATTACHMENT 14 - THERMAL APPRAISAL TEST
Figure 14-1 - Standard Test Chamber
“Exhaust” label for Duct A and “Inlet” label for Duct B deleted to align Figure 14-1
with text of Note 2 as amended by Supplement 5.
ATTACHMENT 16 - RACK CUTOUT
Dimension from lower edge of cutout to datum “K” defined as 0.608 max. on all three
drawings (size 1, size 2, and size 3 connector contents)
SUPPLEMENT 6 TO ARINC SPECIFICATION 600 – Page b
ATTACHMENT 19 - CONNECTOR SPECIFICATION
19.3.5.1
Forces
Note added by this Supplement.
Table 19.5.1 - Performance Verification Tests
“X” added in sample group column D of table for “Engaging Force (with contacts)”
and “Low Level Circuit” tests. (Supplement 5 correction.)
Figure 19-41
Note 3 added. (Supplement 5 correction.)
Figure 19-42
Note 3 added. (Supplement 5 correction.)
Figure 19-43
Note 3 added. (Supplement 5 correction.)
Figure 19-44
Dimension from connector foot (datum “K”) to shell defined as 0.620 min. Note 3
added. (Latter is Supplement 5 correction.)
Figure 19-45
Note 3 added. (Supplement 5 correction)
Figure 19-46
Note 3 added. (Supplement 5 correction.)
Figure 19-54.2
Federal Specification numbers for brass and beryllium (QQ-B-626 and QQ-C-530
respectively) added. (Supplement 5 correction.)
Figure 19-60.1
Federal Specification numbers for brass and beryllium added. (Supplement 5
correction.)
Figure 19-60.2
Federal Specification numbers for brass and beryllium added. (Supplement 5
correction.)
Figure 19.63
SCD 10-61953/12 reference deleted. (Supplement 5 correction)
Figure 19-63.1
Note 10 added. (Supplement 5 correction.)
Figure 19-67
Note 9 added. (Supplement 5 correction.)
Figure 19-68
Note 1 corrected and Note 11 added. (Supplement 5 corrections.)
Figure 19-69
Note 2 corrected and Note 9 added. (Supplement 5 corrections.)
Figure 19-69.1
Note 10 added. (Supplement 5 correction)
Figure 19-70
Figure 19-72.1 reference corrected to 19-72.2 and Note 11 added. (Supplement 5
corrections.)
SUPPLEMENT 6 TO ARINC SPECIFICATION 600 – Page c
Figure 19-70.1
Note 11 added. (Supplement 5 correction.)
Figure 19-71
References in Notes 1 and 6 to Figure 19-45 and SCD 10-61953/22 corrected to
Figure 19-43 and Figure 19-72.1 respectively. (Supplement 5 corrections.)
Figure 19-72
References in Notes 1 and 6 to Figure 19-46 and SCD 10-61953/22 corrected to
Figure 19-44 and Figure 19-72.1 respectively. (Supplement 5 corrections.)
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 7
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: December 26, 1986
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
October 8, 1986
SUPPLEMENT 7 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces details for two new inserts to ARINC 600 connectors.
The first is an insert (Upper and Middle cavity) for two size 1 RF contacts. The
second insert (Lower cavity) is designed to contain 80 number 22 signal pins, 4
number 20 power pins, and 1 number 16 ground pin. Also, an inverted version of the
insert with 1 coax and 70 power pins is included. These inserts are used in the MLS
receiver processor. Also the language describing the choice of pins vs sockets in
receptacle/plug is clarified.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod colored paper, is the
Supplement itself. It contains descriptions of the changes introduced into the
Specification and, where appropriate, extracts from the original text for comparison
purposes. The second part consists of replacement white pages for the
Specification, modified as required by the Supplement. The modified and added
material on each replacement page is identified with “c-7” symbols in the margins.
Existing copies of Specification 600 may be updated by simply inserting the
replacement white pages where necessary and destroying the pages they displace.
The goldenrod colored Supplement should be inserted inside the rear cover of the
Specification, following Supplement 6.
Copies of the Specification bearing the number 600-7 already contain this
Supplement and thus do not require revisions by the reader.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change, for other than very minor revisions, any text originally contained in the
Specification is reproduced for reference.
3.3.5.1
The LRU Electrical Interface
Text was revised to clarify the choice of pins vs sockets in LRU receptacles and rack
mounted plugs.
ATTACHMENT 11 – CONTACT POSITION IDENTIFICATION and INSERT SIZE
The basic presentation of Figures 11-1, 11-2, 11-3, 11-5, 11-7, and 11-9 was
changed. Figures 11-4, 11-6, and 11-8 were added.
ATTACHMENT 17 – CONNECTOR ENGAGING POSITION
Notes 5 and 6 were added.
ATTACHMENT 19 – CONNECTOR SPECIFICATION
Figures 19-49.1, 19-49.2, 19.69.2, and 19.70.2 were added.
19.3.5.3.2 Contact Location
Revised text describing selection of pins vs sockets for use in connector
receptacle/plug.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 8
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: January 23, 1991
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
November 8, 1990
SUPPLEMENT 8 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces a new four-contact connector insert for TCAS
applications. It also introduces minor editorial corrections (e.g. labeling of the
contacts in the 2-contact RF insert shown in Figure 11-4 of Attachment 11). It
includes typical assembly instructions for the size 1 RF contact.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod colored paper, is the
Supplement itself. It contains descriptions of the changes introduced into the
Specification and, where appropriate, extracts from the original text for comparison
purposes. The second part consists of replacement white pages for the
Specification, modified as required by the Supplement. The modified and added
material on each replacement page is identified with “c-8” symbols in the margins.
Existing copies of Specification 600 may be updated by simply inserting the
replacement white pages where necessary and destroying the pages they displace.
The goldenrod colored Supplement should be inserted inside the rear cover of the
Specification.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change is included.
ATTACHMENT 11 – CONTACT POSITION IDENTIFICATION and INSERT SIZE
Figure 11-4 was revised to correct the labeling of the contacts C1 and C2, which
were previously reversed in this illustration.
Figure 11-10 was added to document a new insert providing four size 1 RF contacts.
ATTACHMENT 19 – CONNECTOR SPECIFICATION
The Table of Contents for Attachment 19 was updated to include the new figures
added by this Supplement and minor editorial changes.
Figure 19-49.3 was added to document the contact dimensions of the new of the
new insert providing four size 1 RF contacts.
Figure 19-54.4 was added to document the socket (female) end of the new size 1 RF
contact.
Figure 19-49.5 was added to document the pin (male) end of the new size 1 RF
contact.
Figures 19-54.6-1, 19-54.6-2, and 19-54.6-3 were added to document the receptacle
crimp termination socket (female) assembly of the new size 1 RF contact.
Figure 19-70.3 was added to document the connector profile of the new size 1 RF
contact when used in a size 3 connector (e.g. the TCAS computer unit).
APPENDIX 3 - TYPICAL ASSEMBLY INSTRUCTORS, SIZE 1 RF CONTACT
New appendix added which describes assembly instructions for size 1 RF contacts.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 9
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: November 13, 1992
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
November 4, 1992
SUPPLEMENT 9 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces details for twelve new ARINC 600 connector insert
arrangements to support power and ARINC 629 Data Bus requirements for new
aircraft. It also introduces a change to section 19.3.5.3.2, Contact Location. This
change allows for aircraft built prior to Supplement 7 to maintain compliance with
ARINC 600 and provides the required changes needed for the new connector inserts
in the ARINC 727 Microwave Landing System (MLS) receiver processor. This
Supplement also introduces minor editorial corrections (e.g., labeling of size 1
coaxial contacts in Figure 11-5 of Attachment 11, labeling of size 1 coaxial contacts
in Figures 19-49 and 19-49.1 of Attachment 19, and renumbering of the Contact
Arrangement in Figure 19-49.3 of Attachment 19).
B. ORGANIZATION OF THIS DOCUMENT
The first part of this document, printed on goldenrod colored paper, is the
Supplement itself. It contains descriptions of the changes introduced into the
Specification and, where appropriate, extracts from the original text for comparison
purposes. The second part consists of replacement white pages for the
Specification, modified as required by the Supplement. The modified and added
material on each replacement page is identified with “c-9” symbols in the margins.
Existing copies of ARINC Specification 600 may be updated by simply inserting the
replacement white pages where necessary and destroying the pages they displace.
The goldenrod colored Supplement should be inserted inside the rear cover of the
Specification.
C. CHANGES TO SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is identified
either by the section number and title currently employed in the Specification or by
the section number and title that will be employed when the supplement is eventually
incorporated. In each case there is included a brief description of the addition or
change is included.
ATTACHMENT 11 – CONTACT POSITION IDENTIFICATION and INSERT SIZE
Figures 11-5 and 11-6 were revised to change the labeling of the size 1 coaxial
contact from “C1” to “71”. This is to correct redundant labeling since C1 is already
referenced as a size 22 contact located in column “C” row “1”.
ATTACHMENT 19 – CONNECTOR SPECIFICATION
Section 19.3.5.3.2, “Contact Location”, was changed back to the wording in
Supplement 5 with an exception paragraph added (with the wording of Supplement
7) for the Microwave Landing System (MLS).
Figure 19-49 was revised to add reference “71” for the size 1 coaxial contact in
Contact Arrangement 05.
Figure 19-49.1 was revised to change the labeling of the size 1 coaxial contact from
“c1” to “71”. This is to correct redundant labeling since C1 is already referenced as a
size 22 contact located in column “C” row “1”.
Figure 19-49.3 was changed from Contact Arrangement 10 to Contact Arrangement
11.
Figure 19-49.4 was added to document the contact dimensions of the new insert
providing ten size 8 RF contacts.
Figure 19-49.5 was added to document the contact dimensions of the new insert
providing six size 8 RF contacts.
SUPPLEMENT 9 TO ARINC SPECIFICATION 600 – Page b
Figure 19-49.6 was added to document the contact dimensions of the new insert
providing 118 size 22 signal contacts and two size 8 RF contacts.
Figure 19-49.7 was added to document the contact dimensions of the new insert
providing 110 size 22 signal contacts, six size 20 power contacts, and five size 16
power contacts.
Figure 19-49.8 was added to document the contact dimensions of the new insert
providing 24 size 20 power contacts and ten size 16 power contacts.
Figure 19-49.9 was added to document the contact dimensions of the new insert
providing 60 size 20 power contacts.
Figure 19-49.10 was added to document the contact dimensions of the new insert
providing six size 8 power contacts.
Figure 19-49.11 was added to document the contact dimensions of the new insert
providing 40 size 22 signal contacts.
Figure 19-49.12 was added to document the contact dimensions of the new insert
providing 28 size 22 signal contacts and two size 8 RF contacts.
Figure 19-49.13 was added to document the contact dimensions of the new insert
providing four size 12 power contacts.
Figure 19-49.14 was added to document the contact dimensions of the new insert
providing 50 size 22 signal contacts, five size 16 power contacts, and four size 12
power contacts.
Figure 19-49.15 was added to document the contact dimensions of the new insert
providing 100 size 22 signal contacts, five size 20 power contacts, and five size 12
power contacts.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 10
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: November 20, 1995
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
November 2, 1995
SUPPLEMENT 10 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces two connector insert arrangements for inclusion in
Attachment 19.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod colored paper, contains
descriptions of changes introduced into this report by this Supplement. The second
part consists of replacement white pages for the report modified to reflect the
changes. The modified and added material on each replacement page is identified
with “c-10” symbols in the margins. Existing copies of ARINC Specification 600-9
may be updated by simply inserting the replacement white pages where necessary
and destroying the pages they replace. The goldenrod colored pages is inserted
inside the rear cover of the report.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete tabulation of the changes and additions to the
report introduced by this Supplement. Each change or addition is defined by the
Section number and the title that will be employed when the Supplement is
eventually incorporated. In each case a brief description of the change or addition is
included.
ATTACHMENT 19 – CONNECTOR SPECIFICATION
Figure 19-52.3, Contact Arrangement 24, includes four size 8 RF contacts and
twenty size 20 power contacts.
Figure 19-52.4, Contact Arrangement 25, includes two size 1 RF contacts. This
contact arrangement is similar to Contact Arrangement 9 with the markings “C1” and
“C2” reversed.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 11
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: November 10, 1997
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
October 16, 1997
SUPPLEMENT 11 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement updates the dimensioning and tolerances in ARINC Specification
600. New drawings have been prepared based on two standards, ASME Y14.5M1994 Dimensioning and Tolerance, and ANSI Y14.5.1M-1994 Mathematical
Definition of Dimensioning and Tolerance Principles. Attachments 2, 3, 5, 7, 8, 9, 15,
and 16 have been replaced in their entirety. Attachment 19 was modified to add the
definitions of insert arrangements 26, 27, and 28, and to updates the frequency
range of the size 5 coaxial electrical contact pin and socket.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod colored paper, contains
descriptions of changes introduced into this report by this Supplement. The second
part consists of replacement white pages for the report modified to reflect the
changes. The modified and added material on each replacement page is identified
with “c-11” symbols in the margins. Existing copies of ARINC Specification 600-10
may be updated by simply inserting the replacement white pages where necessary
and destroying the pages they replace. The goldenrod colored pages are inserted
inside the rear cover of the report.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This Section presents a complete tabulation of the changes and additions to the
report introduced by this Supplement. Each change or addition is defined by the
Section number and the title that will be employed when the Supplement is
eventually incorporated. In each case a brief description of the change or addition is
included.
1.4.7 Standard International (S.I.) Units
Commentary was added discussing conversions of tolerances from standard (metric)
to imperial (inch) units.
ATTACHMENT 2 – STANDARD LRU CASE SIZE
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
ATTACHMENT 3 – LOCATION OF CONNECTOR
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
ATTACHMENT 5 – RACK/SHELF DATUMS
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
ATTACHMENT 7 – RACK/LRU HOLD DOWN MECHANISMS
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
ATTACHMENT 8 – LRU GUIDE DIMENSIONS
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
ATTACHMENT 9 – COOLING APERTURES
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
SUPPLEMENT 11 TO ARINC SPECIFICATION 600 – Page b
ATTACHMENT 15 – MCU BACKPLATE CONNECTOR CUTOUT
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
ATTACHMENT 16 – RACK OR TRAY BACKPLATE CONNECTOR CUTOUT
This attachment was replaced by a new attachment with updated drawings based on
ASME and ANSI drawing and dimensioning standards.
ATTACHMENT 19 – CONNECTOR SPECIFICATION
Figure 19-52.5, Contact Arrangement 26, Size 20 HD and Size 22, Shell Size 2 and
3 Connector was added to document the contact dimensions of the new insert
providing 4 size 20 HD and 80 size 22 contacts.
Figure 19-52.6, Contact Arrangement 27, Size 5 Coaxial, Shell Size 1 Connector
was added to document the contact dimensions of the new insert providing 4 size 5
coaxial contacts.
Figure 19-52.7, Contact Arrangement 28, Size 16 and Size 12, Shell Size 2 and 3
Connector was added to document the contact dimensions of the new insert
providing 2 size 16 and 8 size 8 contacts.
Figures 19-60.1 and 19-60.2 were modified to update the frequency range of the
size 5 coaxial electrical contact pin and socket.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 12
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: November 10, 1998
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
April 29, 1998
SUPPLEMENT 12 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement contains corrections to the size of the connector mounting holes
and other dimensions in Attachment 15 and 16 introduced in Supplement 11. This
will make the new dimensioned drawings consistent with previous versions of ARINC
Specification 600.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod colored paper, contains
descriptions of changes introduced into this report by this Supplement. The second
part consists of replacement white pages for the report modified to reflect the
changes. The modified and added material on each replacement page is identified
with “c-12” symbols in the margins. Existing copies of ARINC Specification 600-10
may be updated by simply inserting the replacement white pages where necessary
and destroying the pages they replace. The goldenrod colored pages are inserted
inside the rear cover of the report.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This Section presents a complete tabulation of the changes and additions to the
report introduced by this Supplement. Each change or addition is defined by the
Section number and the title that will be employed when the Supplement is
eventually incorporated. In each case a brief description of the change or addition is
included.
ATTACHMENT 15 – MCU BACKPLATE CONNECTOR CUTOUT
Replaced by new attachment with updated drawings containing corrected
dimensions for connector mounting holes. This will make the new dimensioned
drawings introduced in Supplement 11 consistent with previous versions of ARINC
Specification 600.
ATTACHMENT 16 – RACK OR TRAY BACKPLATE CONNECTOR CUTOUT
Replaced by new attachment with updated drawings containing correct dimensions
for connector mounting holes and other dimensions. This will make the new
dimensioned drawings introduced in Supplement 11 consistent with previous
versions of ARINC Specification 600.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 13
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: March 30, 2001
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
November 14, 2000
SUPPLEMENT 13 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement contains insert arrangements for the mini and standard expanded
beam fiber optic assembly, additional plug and receptacle positions for index pin
coding and new letter designations for datum planes and mounting holes. The insert
arrangement shown as one, two, three, four, and six positions to house a miniexpanded beam insert assembly in size 1, cavity A or B (2, 4, or 6 expanded beam
fiber optic channels) is shown. A similar insert arrangement in size 1, cavity C is also
included. The insert arrangement shown as one, two or three positions to house a
standard expanded beam insert assembly in sizes 2 or 3, cavities A, B, D or E (2, 4
or 6 expanded beam fiber optic channels) is shown. A similar insert arrangement in
size 2 or 3, cavities C or F is also included. An error was corrected in the location of
mounting holes in the shelf/rack cutout. New letter designations were assigned to
eliminate possible confusion in the LRU to mounting tray interface.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod colored paper, contains
descriptions of changes introduced into this Specification by this Supplement. The
second part consists of replacement white pages for the Specification modified to
reflect the changes. The modified and added material on each replacement page is
identified by a “c13” in the margins. Existing copies of ARINC Specification 600-12
may be updated by simply inserting the replacement white pages where necessary
and discarding the pages they replace. The golden-rod pages are inserted inside the
rear cover of the Specification.
C. CHANGES TO ARINC SP CIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This Section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is defined by
the section number and the title that will be employed when the Supplement is
eventually incorporated. In each case a brief description of the change or addition is
included.
ATTACHMENT 3 - LOCATION OF CONNECTOR
Datum S was added to the Front View of shelf/rack and Datum H to the Rear View of
the unit.
ATTACHMENT II - CONTACT POSITION IDENTIFICATION AND INSERT SIZE
Insert arrangements for the mini and standard expanded beam fiber optic
assemblies were added to Attachment 11. These arrangements are for the minexpanded beam in size 1 and the standard expanded beam in sizes 2 and 3.
ATTACHMENT 15 - LRU MOUNTING PATTERN - SIZE 1 CONNECTOR
The word “MAXIMUM” was applied to the radius value 8X R7.29 [.287] on diagrams
showing connector mounting patterns for 2 through 12. and 3 through 12 MCUs. The
box encompassing this value was appropriately removed.
ATTACHMENT 16 - SHELF/RACK CUTOUT – SIZE 2 CONNECTOR
The dimension locating the lower set of mounting holes from Datum K was changed
from 9.14 [.360] to 9.65 [.380] in the three diagrams showing two, four and six
mounting holes. Corresponding value 4X170.43 [6.710] was changed to 4X170.94
[6.730].
SUPPLEMENT 13 TO ARINC SPECIFICATION 600 – Page b
ATTACHMENT 18 - INDEX PIN CODING
Plug and receptacle positions for index pin coding were added for positions from 100
to 216.
ATTACHMENT 19 - CONNECTOR SPECIFICATION
Figure 19-41- Datum B was changed to Datum H.
Figure 19-42 - Datum K was changed to Datum S.
Figure 19-43 - Datum B was changed to Datum H.
Figure 19-44 - Datum K was changed to Datum S.
Figure 19-45 - Datum B was changed to Datum H.
Figure 1946 - Datum K was changed to Datum S.
Figure 19-67 - Datum B was changed to Datum H.
Figure 19-68 - Datum K was changed to Datum S.
Figure 19-69 - Datum B was changed to Datum H.
Figure 19-69.1- Datum B was changed to Datum H.
Figure 19-69.2 - Datum B was changed to Datum H.
Figure 19-70 - Datum K was changed to Datum S.
Figure 19-70.1- Datum K was changed to Datum S.
Figure 19-70.2 - Datum K was changed to Datum S.
Figure 19-70.3 - Datum S was added to the tip of the lower tab of the connector.
Figure 19-71 - Datum B was changed to Datum H.
Figure 19-72 - Datum S was added to the tip of the lower tab of the connector.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 14
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: March 15, 2004
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
October 15, 2003
SUPPLEMENT 14 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement contains the definition of standards for quadrax contacts and
connector inserts. This Supplement also contains standards for twinax contacts that
complement twinax insert definitions already defined in this Specification. These two
connectors, quadrax and twinax, are candidates to be used in Ethernet LAN
installations. This Supplement introduces guidance for qualification testing to ensure
compatibility with Ethernet use. Coaxial contacts were added.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on goldenrod colored paper, contains
descriptions of changes introduced into this Specification by this Supplement. The
second part consists of replacement white pages for the Specification modified to
reflect the changes. A “c-14” in the margins identifies the modified and added
material on each replacement page. The goldenrod pages are inside the rear cover
of the Specification.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This Section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. The section number and the title that
will be employed when the Supplement is eventually incorporated define each
change or addition. In each case, a brief description of the change or addition is
included.
ATTACHMENT 19 – CONNECTOR SPECIFICATION
Figures 19-73.1, 19-73.2, 19-74.1 and 19-74.2 added to describe 75 Ohm coaxial
contacts.
Figures 19-75.1, 19-75.2, 19-76.1 and 19-76.2 added to describe 50 Ohm coaxial
contacts.
ATTACHMENT 20 – CONNECTOR ELECTRICAL AND MECHANICAL
CHARACTERISTICS SIZE 8 QUADRAX TYPE
This attachment was added to provide electrical and mechanical performance
criteria for the quadrax contacts.
ATTACHMENT 21 – CONNECTOR ELECTRICAL AND MECHANICAL
CHARACTERISTICS SIZE 8 TWINAX TYPE
This attachment was added to provide performance criteria for the twinax contacts.
APPENDIX 4 – GUIDELINES FOR AVIONIC 10/100BASE-T ETHERNET CONNECTOR
CHARACTERISTICS
This Appendix was added to provide qualification test parameters and maximum
attenuation for 10/100Base-T Ethernet connectors.
APPENDIX 5 – GUIDANCE FOR USE OF TWINAX AND QUADRAX CONTACTS
New appendix added.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 15
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: January 1, 2006
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
October 4, 2005
SUPPLEMENT 15 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS SUPPLEMENT
This Supplement introduces new inserts accommodating fiber optic termini defined
by ARINC Specification 801. It also defines a new Quadrax insert.
B. ORGANIZATION OF THIS SUPPLEMENT
The first part of this document, printed on golden-rod paper contains descriptions of
changes introduced into this Characteristic by this Supplement. The second part
consists of replacement white pages for the Characteristic, modified to reflect the
changes. The modified and added material on each page is identified by a “c-15” in
the margins. Existing copies of ARINC Specification 600 may be updated by simply
inserting the replacement white pages where necessary and discarding the pages
they replace. The golden-rod pages are inserted inside the rear cover of the
Specification.
C. CHANGES TO ARINC SPECIFICATION 600
This section presents a complete tabulation of the changes and additions to the
Specification introduced by this Supplement. Each change or addition is defined by
the section number and the title that will be employed when the Supplement is
eventually incorporated. In each case a brief description of the change or addition is
included.
ATTACHMENT 19 - CONNECTOR SPECIFICATION
Figures 19-49.16, 19-49.17, 19-49.18 and 19-49.19 were added to the Specification.
ATTACHMENT 20 – CONNECTOR ELECTRICAL AND MECHANICAL
CHARACTERISTICS - SIZE 8 QUADRAX TYPE
Figure 20-6.4 – 62Q2 changed to 64Q2.
Figure 20-6.5 – 68Q2 changed to 70Q2.
Figures 20-6.5.4 and 20-6.5.5 were added.
What follows is draft material that will appear
in the replacement white pages of the
adopted version of this Supplement.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 16
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: November 22, 2006
Prepared by the Airlines Electronic Engineering Committee
Adopted by the Airlines Electronic Engineering Committee:
October 11, 2006
SUPPLEMENT 16 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS DOCUMENT
This Supplement provides corrections to dimension units in Attachment 20.
B. ORGANIZATION OF THIS SUPPLEMENT
In the past, changes introduced by a Supplement to an ARINC Standard were
identified by vertical change bars with an annotation indicating the change number.
Electronic publication of ARINC Standards has made this mechanism impractical.
In this document blue bold text is used to indicate those areas of text changed by
the current Supplement only.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete listing of the changes to the document introduced
by this Supplement. Each change is identified by the section number and the title as
it will appear in the complete document. Where necessary, a brief description of the
change is included.
ATTACHMENT 20 - CONNECTOR ELECTRICAL AND MECHANICAL
CHARACTERISTICS SIZE 8 QUADRAX TYPE
Dimensions in inches removed from the drawings and a note added to indicate that
all dimensions are in millimeters for Figures 20-6.1.1, 20-6.1.2, 20-6.1.3, 20-6.2.1,
20-6.2.2, and 20-6.2.3.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 17
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: February 16, 2010
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
October 28, 2009
SUPPLEMENT 17 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS DOCUMENT
This supplement provides guidance material for positioning fiber optics contacts.
B. ORGANIZATION OF THIS SUPPLEMENT
In the past, changes introduced by a supplement to an ARINC Standard were
identified by vertical change bars with an annotation indicating the change number.
Electronic publication of ARINC Standards has made this mechanism impractical.
In this document blue bold text is used to indicate those areas of text changed by
the current supplement only.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete listing of the changes to the document introduced
by this supplement. Each change is identified by the section number and the title as
it will appear in the complete document. Where necessary, a brief description of the
change is included.
3.3.2.12 Fiber Optic Termini (ARINC 801)
New section and subsections added.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 18
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: May 10, 2010
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
March 31, 2010
SUPPLEMENT 18 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS DOCUMENT
This Supplement provides guidance material for positioning quadrax contacts and
contact cavities in electrical connectors for aircraft use. It provides dimensions and
tolerances to use #8 quadrax in existing connectors, and modifies the spacing
required for positioning the quadrax in the connectors.
This Supplement also specifies the dimensions for keyways in several types of
connectors related to the quadrax insert arrangements.
B. ORGANIZATION OF THIS SUPPLEMENT
In the past, changes introduced by a Supplement to an ARINC Standard were
identified by vertical change bars with an annotation indicating the change number.
Electronic publication of ARINC Standards has made this mechanism impractical.
In this document blue bold text is used to indicate those areas of text changed by
the current Supplement only.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete listing of the changes to the document introduced
by this Supplement. Each change is identified by the section number and the title as
it will appear in the complete document. Where necessary, a brief description of the
change is included.
ATTACHMENT 19
In Attachment 19, the use of #8 quadrax in shell sizes 1,2, and 3 has been changed
with regards to the true position of size #8 quadrax (from .020 to .012 inches).
Figure 19-67 – Intermateability, Shell Size 1 – Receptacle
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.7
Note 8 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 10) to be located within
.020 true position dia.” This directs reader to note 10, which defines the #8
quadrax exception.
Note 10 added to read: “All size #8 quadrax cavities to be located within
0.012 true position dia.”
Figure 19-68 – Intermateability, Shell Size 1 – Plug
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.7
Note 7 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 12) to be located within
.020 true position dia.” This directs reader to note 12, which defines the #8
quadrax exception.
Note 12 added to read: “All size #8 quadrax cavities to be located within
0.012 true position dia.”
Figure 19-69 – Intermateability, Shell Size 2 – Receptacle
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.8
SUPPLEMENT 18 TO ARINC SPECIFICATION 600 – Page b
Note 8 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 10) to be located within
.020 true position dia.” This directs reader to note 10, which defines the #8
quadrax exception.
Note 10 added to read: “All size #8 quadrax cavities to be located within .012
true position dia.”
Figure 19-69.1 – Intermateability, Shell Size 2 – Receptacle with Size 1 Coax
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.8
Note 8 amended to read: “All contact cavities in section C (Except #8
quadrax, see Notes 5 and 11) to be located within .020 true position dia.”
This directs reader to note 11, which defines the #8 quadrax exception.
Note 11 added to read: “All size #8 quadrax cavities in section C to be
located within .012 true position dia.”
Figure 19-69.2 – Intermateability, Shell Size 2 – Receptacle with Size 1 Coax
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.8
Note 8 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 10) to be located within
.020 true position dia.” This directs reader to note 10, which defines the #8
quadrax exception.
Note 10 added to read: “All size #8 quadrax cavities to be located within .012
true position dia.”
Figure 19-70 – Intermateability, Shell Size 2 Plug
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.8
Note 7 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 12) to be located within
.020 true position dia.” This directs reader to note 12, which defines the #8
quadrax exception.
Note 12 added to read: “All size #8 quadrax cavities to be located within .012
true position dia.”
Figure 19-70.1 – Intermateability, Shell Size 2 – Plug with Size 1 Coax
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.8
Note 7 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 12) to be located within
.020 true position dia.” This directs reader to note 12, which defines the #8
quadrax exception.
Note 12 added to read: “All size #8 quadrax cavities to be located within .012
true position dia.”
Figure 19-70.2 – Intermateability, Shell Size 2 – Plug with Size 1 Coax
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.8
SUPPLEMENT 18 TO ARINC SPECIFICATION 600 – Page c
Note 7 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 12) to be located within
.020 true position dia.” This directs reader to note 12, which defines the #8
quadrax exception.
Note 12 added to read: “All size #8 quadrax cavities to be located within .012
true position dia.”
Figure 19-71 – Intermateability, Shell Size 3 - Receptacle
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.8
Note 8 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 12) to be located within
.020 true position dia.” This directs reader to note 12, which defines the #8
quadrax exception.
Note 12 added to read: “All size #8 quadrax cavities to be located within .012
true position dia.”
Figure 19-72 – Intermateability, Shell Size 3 - Plug
Note 5 amended to read: “All #22 contact cavities to be located within a true
position conforming to Figure 19-72.9
Note 7 amended to read: “All contact cavities (Except #22 contact cavities
and #8 quadrax contact cavities, see Notes 5 and 13) to be located within
.020 true position dia.” This directs reader to note 13, which defines the #8
quadrax exception.
Note 13 added to read: “All size #8 quadrax cavities to be located within .012
true position dia.”
ATTACHMENT 20
Figure 20-3.1 – Socket Outer Body #8 Quadrax
Drawing changed to reflect dimension changes/additions:
Dimension “L” added defining the length of which to measure the OD of
socket at 7.31/7.25. Note for “Contact shoulder excluded from dim L” and
Note added to explain the exclusion of hooded contacts
Socket contact insulator dimensions changed from “4.65 max 4.58 min” to
“4.65 max 4.48 min”
Dimension “X” added defining the start of socket time lead-in
Dimension defined for the gap at socket opening
Figure 20-4.1 – Pin Component Shell
Dimension table changed to reflect:
Dimension for #8 quadrax pin depth changed from 11.25/9.60 to 10.60/9.60
(Min/Max), Measurement “A”
Figure 20-4.2 – Socket Component Shell
Drawing changed to reflect dimension addition of the diameter of socket
opening of 5.91 max.
Table changed to reflect #8 quadrax changes from 2.75/1.00 to 2.75/1.65 for
dimension “D” (Max/Min)
SUPPLEMENT 18 TO ARINC SPECIFICATION 600 – Page d
Figure 20-6.1.1 – Plug Front Mounting Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.1.3 – Receptacle Front Mounting Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.2.1 – Plug Front Mounting Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.2.3 – Receptacle Front Mating Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.3.1 – Plug Front Mating Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.3.3 – Receptacle Front Mating Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.4.1 – Plug Front Mating Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.4.3 – Receptacle Front Mating Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.5.1 – Plug Front Mating Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.5.3 – Receptacle Front Mating Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.5.4 – Contact Arrangement 120Q2 Plug Front Mounting Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
Figure 20-6.5.5 –Contact Arrangement 120Q2 Receptacle Front Mounting Face
Dimension added to drawing to define the maximum measurement for the
key on socket opening at 2.00 Max.
AERONAUTICAL RADIO, INC.
2551 Riva Road
Annapolis, Maryland 24101-7435
SUPPLEMENT 19
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: June 23, 2011
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
April 20, 2011
SUPPLEMENT 19 TO ARINC SPECIFICATION 600 – Page a
A. PURPOSE OF THIS DOCUMENT
This Supplement adds clarification to signal and power contacts in arrangement 10
for the 85 insert connector plugs and receptacles. In addition, extensive editorial
changes are made to improve the document.
B. ORGANIZATION OF THIS SUPPLEMENT
In this document blue bold text is used to indicate those areas of text changed by
the current Supplement only. The use of blue bold is only applied to technical
changes, and not to text, table, or format editorial changes.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete listing of the changes to the document introduced
by this Supplement. Each change is identified by the section number and the title as
it will appear in the complete document. Where necessary, a brief description of the
change is included.
ATTACHMENT 2 – STANDARD LRU CASE SIZE
Drawing titled: “STANDARD LRU CASE SIZE”
Note 2 dimension for “maximum LRU rear panel thickness” corrected for
typographical error. 2.54 mm (.00) changed to 2.54 mm (0.100).
ATTACHMENT 17 – CONNECTOR ENGAGING SEQUENCE
Drawing titled “CONNECTOR ENGAGING SEQUENCE”
Mating Sequence 7 dimensions corrected from 0.322 (13.26) to 0.522 (13.26)
Retyped dimension text in this block for clarity
ATTACHMENT 18 – INDEX PIN CODING
Drawing and tables titled “INDEX PIN CODING” clarified.
Notes 1-3 added to clarify applicability.
ATTACHMENT 19 – CONNECTOR SPECIFICATION
In Attachment 19 notes are added to three figures to clarify the 85 insert in
arrangement 10 of Shell size 2 receptacles and plugs.
Figure 19-52.2 – Signal and Power Contact Arrangement 10, Shell Size 2 and 3 Connectors
Note 5 added to read: “Refer to Figures 19-69.2 and 19-70.2 for contact mating tips
dimensions for insert 85 (arrangement 10).”
Figure 19-69.2 – Intermateability, Shell Size 2 – Receptacle with Size 1 Coax
Note 11 added to read: “For insert 85 Arrangement, size 16 contact tip dimensions
are 0.566 / 0.526”.
Added specific dimensions of above note to drawing at mating tips.
Drawing modified for clarity (retyped unreadable text and dimensions at mating tips
area).
Figure 19-70.2 – Intermateability, Shell Size 2 – Plug with Size 1 Coax
Note 13 added to read: “Minimum dimensions for No.16 contact mating tip is 0.190.”
Added specific dimensions of above note to drawing at mating tips.
Drawing modified for clarity (retyped unreadable text and dimensions at mating tips
area).
SAE INDUSTRY TECHNOLOGIES CONSORTIA (SAE ITC)
16701 Melford Blvd., Suite 120
Bowie, Maryland 20715 USA
SUPPLEMENT 20
TO
ARINC SPECIFICATION 600
AIR TRANSPORT AVIONICS EQUIPMENT INTERFACES
Published: July 11, 2017
Prepared by the AEEC
Adopted by the AEEC Executive Committee:
May 30, 2017
SUPPLEMENT 20 TO ARINC SPECIFICATION 600 – Page a
A. A. PURPOSE OF THIS DOCUMENT
This supplement provides corrections or updates to typographical errors.
B. ORGANIZATION OF THIS SUPPLEMENT
In this document, blue bold text is used to indicate those areas of text changed by
the current supplement only.
C. CHANGES TO ARINC SPECIFICATION 600 INTRODUCED BY THIS SUPPLEMENT
This section presents a complete listing of the changes to the document introduced
by this supplement. Each change is identified by the section number and the title as
it will appear in the complete document. Where necessary, a brief description of the
change is included.
Attachment 11
Contact Position Identification and Insert Size
Figure 11-5, Arrangement 05, Shell Size 2 and 3
The figure was incorrectly titled Figure 11-5, Arrangement 05, Shell Size 2.
The figure title was changed to correct the error.
Figure 11-8, Arrangement 10, Shell Size 2
The figure was incorrectly titled Figure 11-8, Arrangement 08, Shell Size 2.
The figure title was changed to correct the error.
Attachment 19
Connector Specification
Section 19.4.5, Mating and Unmating Force
This section was updated to correct a typographical error. The new text reads as
follows:
The maximum amount of direct thrust force to engage or disengage the mating
connector halves should not exceed:
 27 pounds (120N) for Size 1
 60 pounds (267N) for Size 2
 105 pounds (467N) for Size 3
ARINC Standard – Errata Report
1. Document Title
(Insert the number, supplement level, date of publication, and title of the document with the error)
2. Reference
Page Number:
Section Number:
Date of Submission:
3. Error
(Reproduce the material in error, as it appears in the standard.)
4. Recommended Correction
(Reproduce the correction as it would appear in the corrected version of the material.)
5. Reason for Correction (Optional)
(State why the correction is necessary.)
6. Submitter (Optional)
(Name, organization, contact information, e.g., phone, email address.)
Please return comments to standards@sae-itc.org
Note: Items 2-5 may be repeated for additional errata. All recommendations will be evaluated by the staff. Any
substantive changes will require submission to the relevant subcommittee for incorporation into a subsequent
Supplement.
[To be completed by IA Staff ]
Errata Report Identifier:
Review Status:
ARINC Standard Errata Form
June 2014
Engineer Assigned:
Project Initiation/Modification proposal for the AEEC
Date Proposed: Click here to enter a date.
ARINC Project Initiation/Modification (APIM)
1.0
Name of Proposed Project
APIM #: ___________
(Insert name of proposed project.)
1.1
Name of Originator and/or Organization
(Insert name of individual and/or the organization that initiated the APIM)
2.0
Subcommittee Assignment and Project Support
2.1
Suggested AEEC Group and Chairman
(Identify an existing or new AEEC group.)
2.2
Support for the activity (as verified)
Airlines: (Identify each company by name.)
Airframe Manufacturers:
Suppliers:
Others:
2.3
Commitment for Drafting and Meeting Participation (as verified)
Airlines:
Airframe Manufacturers:
Suppliers:
Others:
2.4
Recommended Coordination with other groups
(List other AEEC subcommittees or other groups.)
3.0
Project Scope (why and when standard is needed)
3.1
Description
(Insert description of the scope of the project.)
3.2
Planned usage of the envisioned specification
Note: New airplane programs must be confirmed by manufacturer prior to
completing this section.
New aircraft developments planned to use this specification
Airbus:
(aircraft & date)
Boeing:
(aircraft & date)
Other:
(manufacturer, aircraft & date)
Modification/retrofit requirement
Specify:
(aircraft & date)
Needed for airframe manufacturer or airline project
Specify:
yes ☐ no ☐
yes ☐ no ☐
yes ☐ no ☐
(aircraft & date)
Page 1 of 3
Updated: June 2014
yes ☐ no ☐
Mandate/regulatory requirement
Program and date: (program & date)
Is the activity defining/changing an infrastructure standard?
yes ☐ no ☐
Specify
(e.g., ARINC 429)
When is the ARINC standard required?
______(month/year)__________
What is driving this date? _______(state reason)_____________________
Are 18 months (min) available for standardization work?
yes ☐ no ☐
If NO please specify solution: _________________
Are Patent(s) involved?
yes ☐ no ☐
If YES please describe, identify patent holder: _________________
3.3
Issues to be worked
(Describe the major issues to be addressed.)
4.0
Benefits
4.1
Basic benefits
yes ☐ no ☐
Operational enhancements
For equipment standards:
(a) Is this a hardware characteristic?
yes ☐ no ☐
(b) Is this a software characteristic?
yes ☐ no ☐
(c) Interchangeable interface definition?
yes ☐ no ☐
(d) Interchangeable function definition?
yes ☐ no ☐
If not fully interchangeable, please explain:
Is this a software interface and protocol standard?
_________________
yes ☐ no ☐
Specify: _________________
Product offered by more than one supplier
Identify:
(company name)
yes ☐ no ☐
4.2
Specific project benefits (Describe overall project benefits.)
4.2.1
Benefits for Airlines
(Describe any benefits unique to the airline point of view.)
4.2.2
Benefits for Airframe Manufacturers
(Describe any benefits unique to the airframe manufacturer’s point of view.)
4.2.3
Benefits for Avionics Equipment Suppliers
(Describe any benefits unique to the equipment supplier’s point of view.)
5.0
Documents to be Produced and Date of Expected Result
Identify Project Papers expected to be completed per the table in the following
section.
Page 2 of 3
Updated: June 2014
5.1
Meetings and Expected Document Completion
The following table identifies the number of meetings and proposed meeting days
needed to produce the documents described above.
Activity
Mtgs
Mtg-Days
(Total)
Expected Start
Date
Expected
Completion Date
Document a
# of mtgs
# of mtg days
mm/yyyy
mm/yyyy
Document b
# of mtgs
# of mtg days
mm/yyyy
mm/yyyy
Please note the number of meetings, the number of meeting days, and the
frequency of web conferences to be supported by the IA Staff.
6.0
Comments
(Insert any other information deemed useful to the committee for managing this
work.)
6.1
Expiration Date for the APIM
April/October 20XX
Completed forms should be submitted to the AEEC Executive Secretary.
Page 3 of 3
Updated: June 2014