SSP_50357_Rev_A.doc

SSP 50357 Revision A 30 June 2008

SSP 50357

Node 2 to Crew Quarters

Interface Control Document

International Space Station Program

Revision A

30 June 2008

National Aeronautics and Space Administration

International Space Station Program

Johnson Space Center

Houston, Texas

Contract No. NAS15-10000 European Space Agency

REVISION AND HISTORY PAGE

04-06-99

ERU: /s/ Mary C. Nooney 2-3-09

PREFACE

The contents of this document are intended to be consistent with the tasks and products to be prepared by Program participants. The Crew Quarters to Node 2 Interface Control Document (ICD) shall be implemented on all new International Space Station (ISS) contractual and internal activities and shall be included in any existing contracts through contract changes. This document is under the control of the Space Station Control Board (SSCB) and has delegated future updates and/or revisions to the Multilateral Vehicle Control Board (MVCB).

/s/ Daniel W. Hartman

10/27/08

Daniel W. Hartman

Date

Manager, International Space Station

Vehicle Office

INTERNATIONAL SPACE STATION PROGRAM

Node 2 to Crew Quarters

CONCURRENCE

JSC/EC3

Orgn.

/s/ James Broyan

11 AUG 2008

Signature

Date

JSC/EC6

Manager

Print Name

Orgn.

/s/ Stephanie Walker

Aug. 8, 2008

Signature

Date

JSC/OB

Orgn.

/s/ Daniel W. Hartman

10/27/08

Signature

Date

INTERNATIONAL SPACE STATION PROGRAM

CONCURRENCE

JSC/OB4

Orgn.

/s/ Rafael Garcia

Aug. 28, 2008

Signature

Date

JSC/SF3

Orgn.

/s/ Laura Duvall

Aug. 12, 2008

Signature

Date

ESA

Orgn.

/s/ Philippe Deloo

25 Nov 2008

Signature

Date

INTERNATIONAL SPACE STATION PROGRAM

Interface Control Document

CONCURRENCE

JSC-EC6

PRINT NAME

ORGN

/s/ Ethan Reid

9/4/08

SIGNATURE

DATE

AG-92-J3ES

PRINT NAME

ORGN

/s/ Quentin L. Henry

7/18/08

SIGNATURE

DATE

SUPERVISED BY

(BOEING):

Tony Davis

AG-92-J3ES

PRINT NAME

ORGN

/s/ David J. Brueneman for

7/18/08

SIGNATURE

DATE

DQA BY:

Merry Roberts

AG-92-J3EA

PRINT NAME

ORGN

/s/ Merry Roberts

7/18/08

SIGNATURE

DATE

INTERNATIONAL SPACE STATION PROGRAM

Interface Control Document

LIST OF CHANGES

All changes to paragraphs, tables, and figures in this document are shown below:

SSCBD

ENTRY DATE

CHANGE

PARAGRAPH(S)

None

TABLE(S)

FIGURE(S)

APPENDIX(ES)

Table of Contents

Paragraph Page

1-11.0

INTRODUCTION

1.1 Purpose 1-1 1.2 Scope 1-1 1.3 Precedence 1-1 1.4 Delegation of authority 1-1 1.5 Responsibility and change authority 1-1 2.0

DOCUMENTS

2-1 2.1

APPLICABLE DOCUMENTS

2-1 2.2

REFERENCE DOCUMENTS

2-3 3.0 Interfaces 3-1 3.1

GENERAL

3-1 3.1.1

INTERFACE DESCRIPTION

3-1 3.1.1.1 CQ Description 3-1 3.1.1.2 Node 2 DESCRIPTION 3-2 3.1.2

INTERFACE RESPONSIBILITIES

3-2 3.1.2.1

RESPONSIBILITY FOR CQ

3-2 3.1.2.2 RESPONSIBILITY FOR Node 2 3-2 3.1.2.3 RESPONSIBILITY FOR Interconnect Cabling/Tubing/Connectors 3-2 3.1.3

COORDINATE SYSTEMS

3-2 3.1.4

ENGINEERING UNITS, TOLERANCES, AND CONVERSIONS

3-2 3.1.4.1 Engineering Units and Tolerances 3-2 3.2

INTERFACE REQUIREMENTS

3-3 3.2.1

CQ INTERFACE REQUIREMENTS

3-3 3.2.1.1

ENVELOPE REQUIREMENTS

3-3 3.2.1.2 MASS Properties 3-3 3.2.1.3 STRUCTURAL/MECHANICAL Interface 3-3 3.2.1.4 CQ Fluid Interfaces 3-12 3.2.1.5 Avionics INTERFACES 3-14 3.2.1.6

SOFTWARE INTERFACES

3-34 3.2.1.7 environments 3-34 3.2.2

NODE 2 INTERFACE REQUIREMENTS

3-36 3.2.2.1

ENVELOPE REQUIREMENTS

3-36 3.2.2.2

MASS PROPERTIES

3-37 3.2.2.3

STRUCTURAL/MECHANICAL INTERFACE

3-37 3.2.2.4 Node 2 FLUID INTERFACES 3-37 3.2.2.5 Avionics INTERFACES 3-41 3.2.2.6

SOFTWARE INTERFACES

3-48 3.2.2.7 environments 3-48

Appendices

Paragraph Page

Appendix A Abbreviations and Acronyms A-1

Appendix B Open Work ..........................................................................................................................B-1

List of Figures

Paragraph Page

3-1Figure 3.1.1-1 Node 2 to Crew Quarters Functional Interface Diagram

Figure 3.2.1.1-1 CQ Bump-out Envelope (Side) 3-5 Figure 3.2.1.1-2 CQ Bump-out Envelope (Front) 3-6 Figure 3.2.1.1-3 CQ Bump-out Envelope (Top) 3-7 Figure 3.2.1.1-4 CQ On-orbit Dynamic Envelope (Side) 3-8 Figure 3.2.1.1-5 CQ On-orbit Dynamic Envelope (Top) 3-9 Figure 3.2.1.3.1-1 CQ Utility Interface Plane 3-10 Figure 3.2.1.3.1-2 CQ to Node 2 Connector Interface Locations 3-11 Figure 3.2.1.3.1-3 CQ Utility Cable Take Off Point 3-12 Figure 3.2.1.4.2-1 Ventilation Intakes and Exhaust 3-14 Figure 3.2.1.5.1-1 J1 Power Connector Insert Arrangement 3-15 Figure 3.2.1.5.1-2 J2 Power Connector Insert Arrangement 3-17 Figure 3.2.1.5.2-1 J4 & J5 Hardwire Data Connector Insert Arrangement 3-20 Figure 3.2.1.5.2.2-1 C&DH/SW Functional Layout for CQ #1 (Ovhd) and #2 (Prt) 3-24 Figure 3.2.1.5.2.2-2 C&DH/SW Functional Layout for CQ #3 (Nad) and #4 (Stbd) 3-25 Figure 3.2.1.5.3-1 J3 OPS LAN Connector Insert Arrangement 3-27 Figure 3.2.1.5.5-1 J6 Audio Connector Insert Arrangement 3-29 Figure 3.2.1.5.5-2 J6, ATU Headset Utility Pass Through Pin Definitions 3-31 Figure 3.2.1.5.5.1-1 ATU Audio Headset Interface to Node 2 Crew Quarters 3-33 Figure 3.2.2.4.2.4-1 Node 2 to CQ Ventilation Clear Zones (side) 3-39 Figure 3.2.2.4.2.4-2 Node 2 to CQ Ventilation Clear Zones (front) 3-40

TOC \o "8-8" List of Tables

Paragraph Page

3-3Table 3.1.4.1.1-1 Linear Tolerances

Table 3.2.1.5.1-1 J1 Primary Power Connector Description and Pin Assignments 3-16 Table 3.2.1.5.1-2 J2 Redundant Power Connector Description and Pin Assignments 3-18 Table 3.2.1.5.2-1 J4 Primary Command and Data Handling Description and Pin Assignments 3-21 Table 3.2.1.5.2-2 J5 Redundant Hardwire Data Connector Description and Pin Assignments 3-22 Table 3.2.1.5.2.1-1 Crew Quarters Component Data Signal Characteristics 3-23 Table 3.2.1.5.2.2-1 CQ to Node 2 MDM Interfaces 3-26 Table 3.2.1.5.3-1 J3 OPS LAN Connector Description and Pin Assignments 3-28 Table 3.2.1.5.5-1 J6 Audio Connector Description and Pin Assignments 3-30 Table 3.2.1.7.2-1 Node 2 Vibration Environment 3-35 Table 3.2.1.7.6-1 Crew Quarters Acoustic Noise Limits 3-36 Table 3.2.2.5.6-1 UOP Location 3-43 Table 3.2.2.5.6-2 UOP #1 J3 Connector and Pin Assignments 3-43 Table 3.2.2.5.6-3 UOP #1 J4 Connector and Pin Assignments 3-44 Table 3.2.2.5.6-4 UOP #2 J3 Connector and Pin Assignments 3-45 Table 3.2.2.5.6-5 UOP #2 J4 Connector and Pin Assignments 3-46 Table 3.2.2.5.6-6 UOP #3 J3 Connector and Pin Assignments 3-47 Table 3.2.2.5.6-7 UOP #3 J4 Connector and Pin Assignments 3-48

1.0 INTRODUCTION

1.1 Purpose

The purpose of this document is to define the requirements and the physical, functional, and environmental interfaces between the United States On-Orbit Segment (USOS) Crew Quarters (CQ) and the International Space Station (ISS) Node 2.

1.2 Scope

The scope of this document is limited to the interfaces between the CQ and the Node 2.

1.3 Precedence

In the event of conflict between SSP 41000, System Specification for the International Space Station, and the contents of this Interface Control Document (ICD), the requirements of SSP 41000 shall take precedence.

1.4 Delegation of authority

The National Aeronautics and Space Administration (NASA) may delegate the responsibility for preparation and maintenance of this ICD.

1.5 Responsibility and change authority

This document is prepared and maintained in accordance with SSP 30459, International Space Station Interface Control Plan.

2.0 DOCUMENTS

2.1 APPLICABLE DOCUMENTS

The following documents of the exact issue shown form a part of this document to the extent specified herein. The revising levels of the documents listed herein are not applicable to the Italian Space Agency (ASI).

IEEE/ASTM SI 10-2002

American National Standard for Use of the International System of Units (SI): the Modern Metric System, Appendix B, Section 5.3, “Conversions and Tolerances”

(Reference 3.1.4.1.1)

MIL-STD-1686

Electrostatic Discharge Control Program for Protection of

Rev. C

Electrical and Electronic Parts, Assemblies and Equipment

(Excluding electrically initiated explosive devices)

(Reference 3.2.1.7.1.7, 3.2.2.7.1.7)

MIL-HDBK-263

Electrostatic Discharge Control Handbook for Protection of

Rev. B

Electrical and Electrical Parts, Assemblies, Equipment

(Excluding Electrically Initiated Explosive Devices)(Metric)

(Reference 3.2.1.7.1.7, 3.2.2.7.1.7)

SSP 30237

Space Station Electromagnetic Emissions and

Rev. F

Susceptibility Requirements

(Reference 3.2.1.7.1.2, 3.2.2.7.1.2)

SSP 30238

Space Station Electromagnetic Techniques

Rev. D

(Reference 3.2.1.7.1.2, 3.2.2.7.1.2)

SSP 30240

Space Station Grounding Requirements

(Reference 3.2.1.7.1.3, 3.2.2.7.1.3)

SSP 30242

Space Station Cable/Wire Design and Control

Requirements for Electromagnetic Compatibility

(Reference 3.2.1.7.1.5, 3.2.2.7.1.5)

SSP 30243

Space Station Requirements for Electromagnetic

Rev. G

Compatibility (Reference 3.2.1.7.1.1, 3.2.1.7.1.6, 3.2.1.7.1.8, 3.2.2.7.1.1, 3.2.2.7.1.6, 3.2.2.7.1.8)

SSP 30245

Space Station Electrical Bonding Requirements

(Reference 3.2.1.7.1.4, 3.2.2.7.1.4)

SSP 30257:002

Space Station Program Utility Outlet Panel Standard

Interface Control Document (ICD)

(Reference 3.2.1.5.6, 3.2.2.5.6)

SSP 30260:19

Audio Terminal Unit Standard ICD

(Reference 3.2.1.5.5.1)

SSP 30459

International Space Station Interface Control Plan

Rev. H

(Reference 1.5)

SSP 30482

Electric Power Specifications and Standards:

Vol 1 EPS Electrical Performance Specifications

(Reference 3.2.2.5.1.1)

SSP 30261:002

Space Station Program Space Station Rev. L

Multiplexer/Demultiplexer (SSMDM) Standard Interface Control Document (ICD)

(Reference 3.2.1.5.2, 3.2.2.5.2)

SSP 41000

System Specification for the International Space Station Rev. AY

(Reference 1.3)

SSP 41017

Rack to Mini Pressurized Logistics Module Interface

Part 1

Control Document

Rev. G (Reference 3.1.1.1, 3.2.1.1, 3.2.1.3, 3.2.1.7.3, 3.2.1.7.4, 3.2.1.7.5, 3.2.2.1, 3.2.2.2.1, 3.2.2.3, 3.2.2.7.2, 3.2.2.7.3, 3.2.2.7.4)

SSP 41017

Rack to Mini Pressurized Logistics Module Interface

Part 2

Control Document

Rev. J

(Reference 3.1.1.1, 3.1.3, 3.2.1.3, 3.2.2.3)

SSP 50005

International Space Station Flight Crew Standard

Rev. C

(Reference 3.2.1.3.1.1, 3.2.1.7.1.5, 3.2.2.3.1.1, 3.2.2.7.1.5)

SSP 50290

Prime Item Development Specification for Node 2

Rev. D

(Reference 3.2.2.7.6)

SSP 52051

User Electric Power Specifications and Standards:

Vol. 1

120 Volt DC Loads

(Reference 3.2.1.5.1.1)

SSQ 21635

Connector and Accessories, Electrical, Circular, Miniature, Rev. K

IVA/EVA Compatible, Space Quality, General

Specification for International Space Station Program (Reference 3.2.1.3.1, 3.2.1.5.1, 3.2.1.5.2, 3.2.1.5.3, 3.2.1.5.5, 3.2.2.3.1, 3.2.2.5.1, 3.2.2.5.2, 3.2.2.5.3, 3.2.2.5.5)

2.2 REFERENCE DOCUMENTS

The following documents contain supplemental information to guide the user in the application of this document. These reference documents may or may not be specifically cited within the text of this document.

SSP 50781

Project Technical Requirements Specification for the ISS

Crew Quarters

3.0 Interfaces

3.1 GENERAL

3.1.1 INTERFACE DESCRIPTION

The interfaces specified herein are applicable to the CQ and the Node 2. The Node 2 will provide primary and redundant power, primary and redundant data, Operations Local Area Network (OPS LAN), audio, environmental aisle atmosphere, and structural/mechanical interfaces at the CQ location. The Node 2 also provides Utility Outlet Panel (UOP) power/data for use by the CQ. The functional interface diagram is shown in Figure 3.1.1-1, Node 2 to Crew Quarters Functional Interface Diagram.

Figure 3.1.1-1 Node 2 to Crew Quarters Functional Interface Diagram

3.1.1.1 CQ Description

The CQ is contained in a rack which provides an ISS crew habitation area, rack power switch (RPS), Caution and Warning (C&W), and ventilation fan assemblies. The CQ is fully compatible with the attachment mechanisms and envelopes defined in SSP 41017, Rack to Mini Pressurized Logistics Module Interface Control Document, Parts 1 and 2, with the exception of the bump-out envelopes defined herein. Requirements listed herein are for a single generic CQ volume unless otherwise specified.

3.1.1.2 Node 2 DESCRIPTION

The Node 2 is a pressurized element used as a berthing node for ISS elements and provides accommodations for four CQ (rest, sleep, personal activities, and work).

3.1.2 INTERFACE RESPONSIBILITIES

3.1.2.1 RESPONSIBILITY FOR CQ

Unless otherwise noted herein, Johnson Space Center’s Crew and Thermal Systems Division (JSC/EC), under agreement with the ISS Program Office, has the responsibility for designing the CQ to the interface requirements herein.

3.1.2.2 RESPONSIBILITY FOR Node 2

Unless otherwise noted herein, European Space Agency (ESA) has the responsibility for designing the Node 2 to the interface requirements herein.

3.1.2.3 RESPONSIBILITY FOR Interconnect Cabling/Tubing/Connectors

The Node 2 is responsible for providing interconnecting cabling/connectors to the CQ utility interface location. The CQ is responsible for providing CQ utility interface location connectors.

3.1.3 COORDINATE SYSTEMS

The coordinate system applicable to the Node 2 to CQ interface is as defined in SSP 41017, Part 2, paragraph 3.1.3.

3.1.4 ENGINEERING UNITS, TOLERANCES, AND CONVERSIONS

3.1.4.1 Engineering Units and Tolerances

Dimensions in this document are shown in the English (inch, pound) system of units followed by the equivalent International System (SI) value in parentheses. Measurements may be verified in either system of units.

3.1.4.1.1 Tolerances

Linear tolerances on English dimensions are as indicated in Table 3.1.4.1.1-1, Linear Tolerances. Linear tolerances on metric dimensions are derived from English measurements and tolerances as defined in IEEE/ASTM SI 10–2002, American National Standard for Use of the International System of Units (SI): the Modern Metric System, Appendix B, section 5.3. Angular tolerances are ± 0.1 degrees on all angles unless otherwise stated.

Table 3.1.4.1.1-1 Linear Tolerances

3.2 INTERFACE REQUIREMENTS

3.2.1 CQ INTERFACE REQUIREMENTS

3.2.1.1 ENVELOPE REQUIREMENTS

a. Excluding pop-up and bump-out the CQ shall comply with the envelopes defined in SSP 41017, Part 1, paragraph 3.2.1.1.

b. The CQ shall comply with the on-orbit bump-out and protrusion envelopes defined in Figures 3.2.1.1-1, 3.2.1.1-2, and 3.2.1.1-3, CQ Bump-out Envelopes.

c. The CQ shall comply with the on-orbit dynamic envelope defined in Figures 3.2.1.1-4 and 3.2.1.1-5, CQ On-orbit Dynamic Envelopes.

3.2.1.2 MASS Properties

3.2.1.2.1 MASS

The CQ mass shall be a maximum of 850 pounds. The CQ mass includes connecting hardware defined by 3.1.2.3. The mass does not include crew items brought into or attached to the CQ.

3.2.1.3 STRUCTURAL/MECHANICAL Interface

The CQ structural/mechanical interface description for on-orbit attachment, ground handling attachment, and minimum resonant frequency shall be as defined in SSP 41017, Part 1, paragraph 3.2.1.3.

The CQ structural/mechanical interface is as defined in SSP 41017, Part 2, paragraphs 3.2 and 3.3.

The Crew Quarters will be electrically bonded to Node 2 through Grounding Jumper Assembly 683-56201-2. The coordinates for the Node 2 interface of the CQ rack bonding straps are:

Port CQ: 99.16 (2518,56), -51.47 (1307,41), -41.02 (-1041,98) Overhead CQ: 99.16 (2518,56), 41.02 (1041,98), 51.47 (1307,41) Starboard CQ:99.16 (2518,56), 51.47 (1307,41), -41.02 (-1041,98) Deck CQ: 99.16 (2518,56), 41.02 (1041,.98), -51.47 (-1307,41).

3.2.1.3.1 Utility Interface Location

The CQ interface design shall incorporate a utility interface location for connection of utilities between the CQ and Node 2. The primary functional interface plane is at the CQ utility interface location defined in Figure 3.2.1.3.1-1, CQ Utility Interface Plane. The CQ utility interface location layout and dimensions are defined in Figure 3.2.1.3.1-2, CQ Specific Panel Connector Locations.

A utility cable take-off point shall be defined near the position of the CQ utility interface location. The utility cable lengths shall be measured from the take-off point to the end of the connector shell and shall be 4 feet in length as shown in Figure 3.2.1.3.1-3, CQ Utility Take Off Point.

The CQ shall use connectors as defined herein and be in accordance with SSQ 21635, Connector and Accessories, Electrical, Circular, Miniature, IVA/EVA Compatible, Space Quality, General Specification for International Space Station Program.

3.2.1.3.1.1 Accessibility

The CQ to Node 2 utility interface design shall comply with accessibility requirements of SSP 50005, International Space Station Flight Crew Standard, paragraphs 12.3.1.2 and 12.3.1.3.

Figure 3.2.1.1-1 CQ Bump-out Envelope (Side)

Figure 3.2.1.1-2 CQ Bump-out Envelope (Front)

Figure 3.2.1.1-3 CQ Bump-out Envelope (Top)

Figure 3.2.1.1-4 CQ On-orbit Dynamic Envelope (Side)

Figure 3.2.1.1-5 CQ On-orbit Dynamic Envelope (Top)

Figure 3.2.1.3.1-1 CQ Utility Interface Plane

Figure 3.2.1.3.1-2 CQ to Node 2 Connector Interface Locations

Figure 3.2.1.3.1-3 CQ Utility Cable Take Off Point

3.2.1.4 CQ Fluid Interfaces

3.2.1.4.1 Fire Suppressant

The CQ shall accommodate the application of fire suppressant at each enclosed location containing a potential fire source.

3.2.1.4.2 Temperature and Humidity Control

For the purpose of maintaining crew comfort and life support, the CQ shall obtain air from Node 2 aisle and return CQ air back to the Node 2 aisle as defined in Figure 3.2.1.4.2-1, Ventilation Intakes and Exhaust.

3.2.1.4.2.1 Temperature and humidity control flow rate

The CQ shall receive and return aisle air with Node 2 at a rate between 15 and 180 cubic feet/minute (cfm).

3.2.1.4.2.2 AtmosPHeric heat removal

a. The CQ shall reject a maximum of 165 watts (W) of heat into the Node 2 cabin atmosphere from CQ equipment and crew items brought into the CQ (excluding crew metabolic heat load defined below).

b. The CQ shall reject the average nominal crew metabolic heat load of 135 W, when occupied by a crew member.

3.2.1.4.2.3 Air flow maximum velocity

The airflow velocity at the CQ inlet/outlet shall be less than 250 feet per minute (ft/min).

3.2.1.4.2.4 ventilation keepout zones

The CQ ventilation inlets and outlets shall comply with keep-out zones shown in Figures 3.2.1.1‑1, 3.2.1.1-2, and 3.2.1.1-3.

Figure 3.2.1.4.2-1 Ventilation Intakes and Exhaust

3.2.1.5 Avionics INTERFACES

3.2.1.5.1 RECEIVE primary and redundant POWER

The CQ interface design shall receive primary and redundant 120 volts direct current (VDC) power feeds (3.5 amps each). The CQ to Node 2 electrical power interface shall be at the CQ utility interface location.

The CQ electrical power connectors mounted on the CQ utility interface location using connectors as specified in NASA specification SSQ 21635. The connector insert arrangements are as shown in Figure 3.2.1.5.1-1, J1 Power Connector Insert Arrangement, and Figure 3.2.1.5.1-2, J2 Power Connector Insert Arrangement. The electrical power connectors insert arrangements and pin assignments are shown in Table 3.2.1.5.1-1, J1 Primary Power Connector Description and Pin Assignments and in Table 3.2.1.5.1-2, J2 Redundant Power Connector Description and Pin Assignments.

CONT.

NO.

CONT.

SIZE

LOCATION

Figure 3.2.1.5.1-1 J1 Power Connector Insert Arrangement

Table 3.2.1.5.1-1 J1 Primary Power Connector Description and Pin Assignments

CONNECTOR ID (J1 Primary Power)

PIN FUNCTION TABLE

Figure 3.2.1.5.1-2 J2 Power Connector Insert Arrangement

Table 3.2.1.5.1-2 J2 Redundant Power Connector Description and Pin Assignments

CONNECTOR ID (J2 Redundant Power)

PIN FUNCTION TABLE

3.2.1.5.1.1 POWER QUALITY

The CQ electrical power needs shall comply with the quality standards defined in SSP 52051, User Electric Power Specifications and Standards, Volume 1: 120 VDC Loads for Interface C.

3.2.1.5.1.2 Power Control

Not applicable.

3.2.1.5.1.3 steady-state current

Not applicable.

3.2.1.5.2 Crew Quarters Command and Data Handling (C&DH) INTERFACES

The following CQ components shall exchange non-1553B data with the Node 2 in accordance with SSP 30261:002, Space Station Program Space Station Multiplexer/Demultiplexer (SSMDM) Standard Interface Control Document (ICD):

a. Crew Quarters fan assembly

b. RPS

c. deleted

d. deleted

e. C&W alarm

The CQ to Node 2 Command and Data Handling (C&DH) interface shall be at the CQ utility interface location.

The CQ non-1553B hardwired connectors mounted on the CQ utility interface location are circular NATC07T13N35SN connectors for both the J4 and the J5 location, as specified in NASA specification SSQ 21635. To preclude cross connection, the CQ C&DH connectors mounted on the CQ utility interface location shall each be labeled with a Harness Manufacturing Unit (HMU) number and a unique identification label. The C&DH connector insert arrangement is shown in Figure 3.2.1.5.2-1, J4 & J5 Hardwire Data Connector Insert Arrangement. The C&DH connector pin assignments are shown in Table 3.2.1.5.2-1, J4 Primary Command and Data Handling Description and Pin Assignments and in Table 3.2.1.5.2-2, J5 Redundant Command and Data Handling Description and Pin Assignments.

The non-1553 hardwired signal cable lengths shall be less than 15 ft internal to the CQ.

Figure 3.2.1.5.2-1 J4 & J5 Hardwire Data Connector Insert Arrangement

Table 3.2.1.5.2-1 J4 Primary Command and Data Handling Description and Pin Assignments CONNECTOR ID (J4 Hardwire Data)

PIN FUNCTION TABLE

Table 3.2.1.5.2-2 J5 Redundant Hardwire Data Connector Description and Pin Assignments

CONNECTOR ID (J5 Hardwire Data)

PIN FUNCTION TABLE

3.2.1.5.2.1 COMMAND AND DATA HANDLING CHARACTERISTICS

The characteristics for each CQ component data signal are as defined in Table 3.2.1.5.2.1-1, Crew Quarters Component Data Signal Characteristics.

Table 3.2.1.5.2.1-1 Crew Quarters Component Data Signal Characteristics

1 = Fan Controller GO If in 0 state, no power available or controller is NOGO

If in 1 state, controller is GO

1 = 1 of 2 fans NOGO If in 0 state, both fans available

If in 1 state, only 1 fan available

1 = 2 fans NOGO If in 0 state, at least 1 fan available

If in 1 state, no fans available

1 = Fan Controller GO If in 0 state, no power available or controller is NOGO

If in 1 state, controller is GO

1 = 1 of 2 fans NOGO If in 1 state, only 1 fan available

If in 0 state, both fans available

1 = 2 fans NOGO If in 1 state, no fans available

If in 0 state, at least 1 fan available

1 = Closed If in 0 state, power to be off to Crew Quarter

If in 1 state, power to be on to Crew Quarter

Scarred in Node 2; Not used by CQ

1 = On If in 0 state, indicator lamp is out, no fire indication detected

If in 1 state, indicator lamp is on, fire indication detected

Scarred in Node 2; Not used by CQ

1= Alarm If in 0 state, no alarm asserted

If in 1 state, Class 1 alarm is asserted

1= Alarm If in 0 state, no alarm asserted

If in 1 state, Class 1 alarm is asserted

Note: SW683-70782-1 3.2.1.3.1 FDS Capability Inputs B.

3.2.1.5.2.2 C&DH functionality

The C&DH functionality shall be provided via the CQ utility pass through at the Crew Quarters Utility Interface Location defined herein. This C&DH/ Software (SW) functionality for each CQ is shown in Figures 3.2.1.5.2.2-1, C&DH/SW Functional layout for CQ #1 Overhead (Ovhd) and #2 Port (Prt) and 3.2.1.5.2.2-2, C&DH/SW Functional layout for CQ #3 Nadir (Nad) and #4 Starboard (Stbd), with the CQ to Node 2 Multiplexer/Demultiplexers (MDM) interface definition shown in Table 3.2.1.5.2.2-1, CQ to Node 2 MDM Interfaces. Each CQ shall be responsible for control of the ventilation fans. The CQ firmware controller shall monitor status of fans and report via C&DH normal operating conditions, single fan failures, and dual fan failures. The C&DH shall monitor status from CQ firmware controller and report status as appropriate.

Figure 3.2.1.5.2.2-1 C&DH/SW Functional Layout for CQ #1 (Ovhd) and #2 (Prt)

Figure 3.2.1.5.2.2-2 C&DH/SW Functional Layout for CQ #3 (Nad) and #4 (Stbd) Table 3.2.1.5.2.2-1 CQ to Node 2 MDM Interfaces

* Total per CQ: 12 discrete signals and 2 analog signals.

** Total per Node 2 MDM: 24 DIOs (16-DIO2, 6-DIO3, & 2-DIO4) and 4 LLAs (4-LLAV1).

*** Scarred in Node 2; not used by CQ

3.2.1.5.3 OPERATIONS LOCAL aREA nETWORK (OPS LAN) iNTERFACE

The CQ shall accommodate a Node 2 OPS LAN interface. The CQ to Node 2 OPS LAN interface shall be at the CQ utility interface location.

The CQ OPS LAN connector mounted on the CQ utility interface location is a circular NATC07T11N35SN connector for the J3 location, as specified in NASA specification SSQ 21635. The OPS LAN connector insert arrangement is shown in Figure 3.2.1.5.3-1, J3 OPS LAN Connector Insert Arrangement. The OPS LAN connector insert arrangement and pin assignments are defined in Table 3.2.1.5.3-1, J3 OPS LAN Connector Description and Pin Assignments.

The OPS LAN length shall be less than 15 ft internal to the CQ.

Figure 3.2.1.5.3-1 J3 OPS LAN Connector Insert Arrangement

Table 3.2.1.5.3-1 J3 OPS LAN Connector Description and Pin Assignments

CONNECTOR ID (J3 OPS LAN)

PIN FUNCTION TABLE

3.2.1.5.4 VIDEO INTERFACE

Not applicable.

3.2.1.5.5 Audio Interface

The CQ shall interface with audio from Node 2. The CQ to Node 2 audio interface is at the CQ utility interface location.

The CQ audio connector mounted on the CQ utility interface location is a circular NATC07T13N35PB connector for the J6 location, as specified in NASA specification SSQ 21635. The audio connector insert arrangement is shown in Figure 3.2.1.5.5-1, J6 Audio Connector Insert Arrangement. The audio connector description and pin assignments are defined in Table 3.2.1.5.5-1, J6 Audio Connector Description and Pin Assignments, and Figure 3.2.1.5.5‑2, J6, ATU Headset Utility Pass Through Pin Definitions.

Figure 3.2.1.5.5-1 J6 Audio Connector Insert Arrangement

Table 3.2.1.5.5-1 J6 Audio Connector Description and Pin Assignments

CONNECTOR ID (J6 Audio)

PIN FUNCTION TABLE

Figure 3.2.1.5.5-2 J6, ATU Headset Utility Pass Through Pin Definitions

Audio Functionality

Audio Terminal Unit (ATU) audio headset functionality shall be supplied to each CQ via the utility interface location defined herein. The CQ shall support the ATU interface and signal requirements as per SSP 30260:019, Audio Terminal Unit Standard ICD.

The audio signals are routed from both ATUs in Node 2 through the Node 2 cable HMU-646 to the J6 connector on the CQ utility interface panel as described in section 3.2.1.5.5, Audio Interface. The Crew Quarters will then provide a headset interface connector, J7, which will allow the connection of a Crew Communication Headset Assembly (CCHA) as shown in Figure 3.2.1.5.5.1-1, ATU Audio Headset Interface to Node 2 Crew Quarters. The CQ will pass the signals and data from the CCHA to the ATUs and back from the ATUs to the CCHA. The CCHA electrical signal data and pin assignments are defined in SSP 30260:19, Table D-1 (connector J2), and the CCHA connectors are defined in SSP 30260:19, Figure D-6.

Two CQ can be serviced with ATU audio at a given time. The crew will manually configure the audio jumper to the selected CQ patch panel connector.

Figure 3.2.1.5.5.1-1 ATU Audio Headset Interface to Node 2 Crew Quarters

3.2.1.5.6 UOP Power and Data Interface

The CQ shall provide a connector to accommodate a drag on cable connection from one of three UOPs in Node 2. The UOP interfaces are defined herein and in accordance with SSP 30257:002, Utility Outlet Panel Standard Interface Control Document (ICD).

The Node 2 UOP locations are defined in Table 3.2.2.5.6-1, UOP Location.

3.2.1.5.7 Caution and Warning Functionality

CQ shall receive a primary and redundant DIO3 signal from the Node 2 MDMs for Class 1 alarm indications as shown in Figures 3.2.1.5.2.2-1 and 3.2.1.5.2.2-2. Class 1, 2, and 3 indications may be provided by the ATU audio connection. The CQ Class 1 warning will be annunciated via the redundant CQ Warning Units.

3.2.1.6 SOFTWARE INTERFACES

Not applicable.

3.2.1.7 environments

3.2.1.7.1 electromagnetic radiation

3.2.1.7.1.1 electromagnetic compatibility (EMC) requirements

The CQ shall be designed to be electromagnetically compatible with itself and with other interfacing equipment. The deliverable end item shall meet the requirements of SSP 30243, Space Station Requirements for Electromagnetic Compatibility.

3.2.1.7.1.2 Electromagnetic Interference (EMI) requirements

CQ equipment shall meet the requirements as specified in SSP 30237, Space Station Electromagnetic Emissions and Susceptibility Requirements, and SSP 30238, Space Station Electromagnetic Techniques.

3.2.1.7.1.3 Electrical grounding

Electrical grounding shall be in accordance with SSP 30240.

3.2.1.7.1.4 Electrical bonding

The CQ electrical bonding shall be in accordance with SSP 30245, Space Station Electrical Bonding Requirements. The CQ will be electrically bonded to Node 2 through Grounding Jumper Assembly, as defined in 3.2.1.3. Critical electrical bonds shall be noted on CQ drawings.

3.2.1.7.1.5 Cable/wire design control

Cable/wire design and control shall be in accordance with SSP 30242, Space Station Cable/Wire Design and Control Requirements for Electromagnetic Compatibility, and in SSP 50005, paragraph 11.14.3.

3.2.1.7.1.6 electrostatic discharge

Electrostatic discharge control will be in accordance with SSP 30243, paragraph 3.2.9.

3.2.1.7.1.7 Electrostatic discharge protection

Parts, assemblies, and equipment susceptible to static discharge shall be protected from Electrostatic Discharge (ESD) in accordance with MIL-STD-1686, Electrostatic Discharge Control Program for Protection of Electrical and Electronic Parts, Assemblies and Equipment (Excluding electrically initiated explosive devices). MIL-HDBK-263, Electrostatic Discharge Control Handbook for Protection of Electrical and Electrical Parts, Assemblies, Equipment

(Excluding Electrically Initiated Explosive Devices)(Metric), may be used as a guide.

3.2.1.7.1.8 corona

CQ equipment shall meet the requirements specified in SSP 30243, paragraph 3.2.13.

3.2.1.7.2 Vibration

The CQ shall withstand the vibration environment as defined in Table 3.2.1.7.2-1, Node 2 Vibration Environment, without loss of functionality as defined herein.

Table 3.2.1.7.2-1 Node 2 Vibration Environment

Frequency

(Hz)

PSD

(g2/Hz)

0.001 Slope

(dB/oct)

20-72

5.4

250-2000

-5.1

Composite: 2.2 gRMS

3.2.1.7.3 Acceleration

The CQ shall withstand the accelerations as defined in SSP 41017, Part 1, paragraph 3.2.1.4.2, without loss of functionality.

3.2.1.7.4 CQ Interface LOADS

The CQ shall withstand structural loads as specified in SSP 41017, Part 1, paragraph 3.2.1.4.2, without loss of functionality as defined herein.

3.2.1.7.5 REPRESSURIZATION/DEPRESSURIZATION

The CQ shall withstand a maximum depressurization rate as specified in SSP 41017, Part 1, paragraph 3.2.1.4.4 and maximum repressurization rate of 8 psi/min (920 Pascals per second (Pa/s)).

3.2.1.7.6 On-orbit Acoustics

The CQ shall limit continuous acoustic emissions, measured 60 cm from the loudest external point on the rack to the sound pressure levels (SPL) specified in Table 3.2.1.7.6-1, Crew Quarters Acoustic Noise Limits, equivalent to noise criteria (NC)-40.

Table 3.2.1.7.6-1 Crew Quarters Acoustic Noise Limits

Sound pressure level measured at 0.6 meters distance from the CQ

Octave Band Center Frequency

(Hz) Sound Pressure Level

(dB)

3.2.1.7.7 ATMOSPHERE Interface

3.2.1.7.7.1 atmosphere temperature

The CQ shall operate in an ambient atmosphere temperature of 63 degrees Fahrenheit to 85 degrees Fahrenheit (17.2 degrees Celsius to 29.4 degrees Celsius).

3.2.1.7.7.2 atmosphere pressure

The CQ shall operate in the Node 2 at ambient pressures between 13.9 to 15.2 psia (95.8 kPa to 104.8 kPa).

3.2.1.7.7.3 Atmosphere humidity

The CQ shall operate in an atmosphere with a dew point of 40 degrees Fahrenheit to 60 degrees Fahrenheit (4.5 degrees Celsius to 15.5 degrees Celsius) and a relative humidity between 25 percent and 70 percent.

3.2.2 NODE 2 INTERFACE REQUIREMENTS

3.2.2.1 ENVELOPE REQUIREMENTS

The Node 2 shall reserve volume for the CQ envelopes as defined in SSP 41017, Part 1, paragraph 3.2.2.1.

The Node 2 shall reserve volume for the CQ on-orbit bump-out envelopes as defined in Figures 3.2.1.1-1, 3.2.1.1-2, and 3.2.1.1-3.

3.2.2.2 MASS PROPERTIES

3.2.2.2.1 MASS

The Node 2 shall accommodate a fully outfitted and manned CQ mass as specified in SSP 41017, Part 1, 3.2.2.2. The CQ mass will be per 3.2.1.2.1.

3.2.2.3 STRUCTURAL/MECHANICAL INTERFACE

The Node 2 structural/mechanical interface description shall be as defined in SSP 41017, Part 1, paragraph 3.2.2.3.

The Node 2 structural/mechanical interface shall be as defined in SSP 41017, Part 2, paragraphs 3.2 and 3.3.

3.2.2.3.1 Utility interface location

The Node 2 shall interface with a CQ utility interface location for connection of utilities between Node 2 and CQ. The Node 2 shall use a straight backshell for all connectors.

The Node 2 shall use connectors defined in herein and be in accordance with SSQ 21635.

3.2.2.3.1.1 Accessibility

The Node 2 to CQ utility interface design shall comply with accessibility requirements of SSP 50005, paragraphs 12.3.1.2 and 12.3.1.3.

3.2.2.4 Node 2 FLUID INTERFACES

3.2.2.4.1 Fire suppressant

Not applicable.

3.2.2.4.2 Temperature and Humidity Control

For the purpose of maintaining crew comfort and life support the Node 2 shall supply aisle air for the CQ and receive CQ air back into the aisle as defined in Figure 3.2.1.4.2-1.

3.2.2.4.2.1 Temperature and humidity control flow rate

Not applicable.

3.2.2.4.2.2 Atmospheric heat removal

a. The Node 2 shall receive a maximum of 165 W of heat from CQ equipment and crew items brought into the CQ (excluding crew metabolic heat load defined below).

b. The Node 2 shall receive the average nominal crew metabolic heat load rejected from the CQ of 135 W, when occupied by a crew member.

3.2.2.4.2.3 Air flow maximum velocity

Not applicable.

3.2.2.4.2.4 Ventilation clear zones

The CQ ventilation and exhaust areas shall remain free of obstruction. These areas are defined in Figure 3.2.2.4.2.4-1, Node 2 to CQ Ventilation Clear Zones (side) and Figure 3.2.2.4.2.4‑2, Node 2 CQ Ventilation Clear Zones (front).

<TBD 3-1>

Figure 3.2.2.4.2.4-1 Node 2 to CQ Ventilation Clear Zones (side)

<TBD 3-2>

Figure 3.2.2.4.2.4-2 Node 2 to CQ Ventilation Clear Zones (front)

3.2.2.5 Avionics INTERFACES

3.2.2.5.1 SUPPLY Primary and redundant POWER

The Node 2 shall supply primary and redundant 120 VDC power feeds (3.5 amps each). The Node 2 to CQ electrical power interface shall be at the CQ utility interface location.

The Node 2 primary and redundant power connectors to be connected to the jam nut mount receptacles mounted on the CQ utility interface location using connectors as specified in NASA specification SSQ 21635. The connector insert arrangements are as shown in Figures 3.2.1.5.1-1 and 3.2.1.5.1-2. The electrical power connectors pin assignments are shown in Tables 3.2.1.5.1‑1 and 3.2.1.5.1-2.

3.2.2.5.1.1 power quality

The Node 2 electrical power quality standards shall conform with quality standards defined in SSP 30482, Electrical Power Specifications and Standards, Volume 1: EPS Electrical Performance Specifications, for Interface C.

3.2.2.5.1.2 POWER CONTROL

The Node 2 shall control the supply of power to the CQ.

3.2.2.5.1.3 steady state current

Not applicable.

3.2.2.5.2 CQ C&DH INTERFACES

The Node 2 shall exchange non-1553B data with the following CQ components in accordance with SSP 30261:002:

a. CQ fan assembly

b. RPS

c. deleted

d. deleted

e. Class 1 alarm

The Node 2 C&DH to CQ interface shall be at the CQ utility interface location.

The Node 2 non-1553B hardwired connectors to be connected to the jam nut mount receptacles mounted on the CQ utility interface location using connectors as specified in NASA specification SSQ 21635. To preclude cross connection, the Node 2 C&DH connectors shall be color coded. The C&DH connector insert arrangement is shown in Figure 3.2.1.5.2-1. The C&DH connector pin assignments are shown in Tables 3.2.1.5.2-1 and 3.2.1.5.2-2.

The Node 2 side of the non-1553 hardwired signal cable lengths shall be less than 60 ft between the CQ utility interface location and the Node 2 MDM.

3.2.2.5.2.1 C&DH CHARACTERISTICS

The characteristics for each CQ component data signal are as defined in Table 3.2.1.5.2.1-1.

3.2.2.5.3 ops lAN INTERFACE

The Node 2 shall accommodate an OPS LAN interface with CQ. The CQ to Node 2 OPS LAN interface shall be at the CQ utility interface location.

The Node 2 OPS LAN connector to be connected to the jam nut receptacles mounted on the CQ utility interface location using connectors as specified in NASA specification SSQ 21635. The OPS LAN connector insert arrangement is shown in Figure 3.2.1.5.3-1. The OPS LAN connector insert arrangement and pin assignments are defined in Table 3.2.1.5.3-1.

The Node 2 side of the OPS LAN cable shall be less than 60 ft between the CQ utility interface location and the OPS LAN hub connector.

3.2.2.5.4 video interface

Not applicable.

3.2.2.5.5 audio interface

The Node 2 shall provide for the exchange of audio data between each CQ and an ATU. The Node 2 to CQ audio interface shall be at the CQ utility interface location.

The Node 2 audio connector to be connected to the jam nut mount receptacle mounted on the CQ utility interface location is a circular NATC06G13N35SB connector for the J6 location, as specified in NASA specification SSQ 21635. The audio connector insert arrangement is shown in Figure 3.2.1.5.5-1. The audio connector insert arrangement and pin assignments are defined in Table 3.2.1.5.5-1.

3.2.2.5.6 UOP power and data interface

The Node 2 shall provide 3 UOPs within the Node 2. The UOP interface plane shall be at the UOP. The UOP interface is defined in SSP 30257:002, UOP Standard ICD.

The Node 2 UOP locations are provided in Table 3.2.2.5.6-1, UOP Location. The locations are referenced from the Node 2 coordinate system and are to the center point of the UOP panel facing the cabin area. The three Node 2 UOPs, J3, and J4 connectors and pin assignments are provided in Tables 3.2.2.5.6-2, 3.2.2.5.6-3, 3.2.2.5.6-4, 3.2.2.5.6-5, 3.2.2.5.6-6, and 3.2.2.5.6-7, UOP #1 J3 Connector and Pin Assignments, UOP #1 J4 Connector and Pin Assignments, UOP #2 J3 Connector and Pin Assignments, UOP #2 J4 Connector and Pin Assignments, UOP #3 J3 Connector and Pin Assignments, and UOP #3 J4 Connector and Pin Assignments, respectively.

Table 3.2.2.5.6-1 UOP Location

Port AFT cone #1

147.95

(3757.94) 35.73

(907.48) 17.78

(451.69)

Starboard AFT cone #2

147.95

(3757.94) 35.70

(906.68) -21.33

(-541.67)

Port Deck Standoff #3

125.87

(3197.03)

- 43.01

(-1092.41)

- 43.01

(-1092.41)

Table 3.2.2.5.6-2 UOP #1 J3 Connector and Pin Assignments

UOP #1 (J3-UOP US Core Sys. 1553 Data)

PIN FUNCTION TABLE

Table 3.2.2.5.6-3 UOP #1 J4 Connector and Pin Assignments

UOP #1 (J4-UOP APM PWS (P) 10 Base-T)

PIN FUNCTION TABLE

Table 3.2.2.5.6-4 UOP #2 J3 Connector and Pin Assignments

UOP #2 (J3-No Data)

PIN FUNCTION TABLE

Table 3.2.2.5.6-5 UOP #2 J4 Connector and Pin Assignments

UOP #2 (J4-UOP APM PWS (P) 10 Base-T)

PIN FUNCTION TABLE

Table 3.2.2.5.6-6 UOP #3 J3 Connector and Pin Assignments

UOP #3 (CHeCS 1553 Data)

PIN FUNCTION TABLE

Table 3.2.2.5.6-7 UOP #3 J4 Connector and Pin Assignments

UOP #3 (CHeCS 1553 Data)

PIN FUNCTION TABLE

3.2.2.5.7 Caution and Warning Functionality

Node 2 shall supply primary and redundant Class 1 alarm indications from the MDMs as shown in Figures 3.2.1.5.2.2-1 and 3.2.1.5.2.2-2.

3.2.2.6 SOFTWARE INTERFACES

Not applicable.

3.2.2.7 environments

3.2.2.7.1 electromagnetic Radiation

3.2.2.7.1.1 EMC requirements

The Node 2 shall be designed to be electromagnetically compatible with itself and with other interfacing equipment. The deliverable end item shall meet the requirements of SSP 30243.

3.2.2.7.1.2 EMI requirements

Node 2 equipment shall meet the requirements as specified in SSP 30237 and SSP 30238.

3.2.2.7.1.3 Electrical grounding

Electrical grounding shall be in accordance with SSP 30240.

3.2.2.7.1.4 Electrical bonding

The Node 2 electrical bonding shall be in accordance with SSP 30245. Critical electrical bonds shall be noted on CQ drawings.

3.2.2.7.1.5 Cable/wire design control

Cable/wire design and control shall be in accordance with SSP 30242 and in SSP 50005, paragraph 11.14.3.

3.2.2.7.1.6 electrostatic discharge

ESD control will be in accordance with SSP 30243, paragraph 3.2.9.

3.2.2.7.1.7 Electrostatic discharge protection

Node 2 parts, assemblies, and equipment susceptible to static discharge shall be protected from ESD in accordance with MIL-STD-1686. MIL-HDBK-263 may be used as a guide.

3.2.2.7.1.8 corona

Node 2 equipment shall meet the requirements specified in SSP 30243, paragraph 3.2.13.

3.2.2.7.2 Vibration

The Node 2 interfaces to the CQ shall withstand random vibration environment as defined in Table 3.2.1.7.2-1 without loss of functionality as defined herein.

3.2.2.7.3 Acceleration

The Node 2 interfaces to the CQ shall withstand on-orbit 0.2g structural loads as specified in SSP 41017, Part 1, paragraph 3.2.1.4.2, without loss of functionality as defined herein.

3.2.2.7.4 CQ Interface LOADS

The Node 2 interfaces to the CQ shall withstand structural loads as specified in SSP 41017, Part 1, paragraph 3.2.1.4.3, without loss of functionality as defined herein.

3.2.2.7.5 REPRESSURIZATION/DEPRESSURIZATION

Not applicable.

3.2.2.7.6 On-orbit Acoustics

Node 2 shall provide an on-orbit acoustic environment as specified in SSP 50290, Prime Item Development Specification for Node 2, paragraph 3.3.10.1.

3.2.2.7.7 ATMOSPHERE Interface

3.2.2.7.7.1 atmosphere temperature

The Node 2 shall provide an ambient atmosphere temperature of 63 degrees Fahrenheit to 85 degrees Fahrenheit (17.2 degrees Celsius to 29.4 degrees Celsius).

3.2.2.7.7.2 atmosphere pressure

The Node 2 shall provide ambient pressures between 13.9 to 15.2 psia (95.8 kPa to 104.8 kPa).

3.2.2.7.7.3 Atmosphere humidity

The Node 2 shall provide an atmosphere with a dew point of 40 degrees Fahrenheit to 60 degrees Fahrenheit (4.5 degrees Celsius to 15.5 degrees Celsius) and a relative humidity between 25 percent and 70 percent.

APPENDIX A Abbreviations and Acronyms

APM

Attached Pressurized Module (Columbus)

ATU

Audio Terminal Unit

AWG

American Wire Gage

CCHA

Crew Communication Headset Assembly

CQ

Crew Quarters

C&DH

Command and Data Handling

C&W Caution and Warning

CHeCS Crew Health Care System dB Decibel

EMC

Electromagnetic Compatibility

EMI

Electromagnetic…