LS-71143 - 1/28/00

Space And Life Sciences Criticality 3Experiment Unique Equipment

System Requirements Document

E085/507Visuomotor and Orientation Investigations in

Long-duration Astronauts (VOILA)

LS-71143

Preface

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This experiment specific SRD has been derived from the JSC provided template LS-71143 dated28 February 2000.

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CONTENTS

SectionPage

1.0 SCOPE 1-11.1 GUIDELINES FOR COMPLETION OF THE SYSTEM

REQUIREMENTS DOCUMENT TEMPLATE 1-Error! Bookmark

2.0 APPLICABLE DOCUMENTS 2-22.1 DOCUMENTS 2-22.2 ORDER OF PRECEDENCE 2-5

3.0 SYSTEM REQUIREMENTS 3-13.1 ITEM DEFINITION 3-13.1.1 Experiment Description 3-23.1.1.1 Experiment Overview 3-23.1.1.2 Operational Overview 3-33.2 CHARACTERISTICS 3-43.2.1 Performance Characteristics 3-43.2.1.1 Functional Performance Characteristics 3-43.2.1.2 Equipment Performance Characteristics 3-53.2.2 Physical Characteristics 3-63.2.2.1 Mass Properties 3-63.2.2.2 Envelope 3-63.2.2.2.1 Stowed Envelope 3-63.2.2.2.2 Deployed Envelope 3-73.2.2.2.2.1 Hardware Protrusion Limits 3-73.2.2.2.2.1.1 Permanent Protrusions 3-73.2.2.2.2.1.2 Intermittent Protrusions 3-83.2.2.2.2.1.3 Temporary Protrusions 3-83.2.2.2.2.1.4 Clearance for Crew Restraints and Mobility Aids 3-83.2.2.2.2.2 Deployed Envelope Dimensions 3-93.2.3 Reliability 3-93.2.3.1 Failure Propagation 3-103.2.4 Maintainability 3-103.2.4.1 Logistics and Maintenance 3-113.2.4.1.1 Payload In-Flight Maintenance 3-113.2.4.1.2 Maintenance Functions 3-113.2.5 Environmental Conditions 3-113.2.5.1 On-Orbit Environmental Conditions 3-113.2.5.1.1 On-Orbit Internal Environments 3-113.2.5.1.1.1 Pressure 3-113.2.5.1.1.2 Temperature 3-113.2.5.1.1.3 Humidity 3-12

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CONTENTS (Cont'd)

SectionPage3.2.5.1.2 Use of Cabin Atmosphere 3-123.2.5.1.2.1 Active Air Exchange 3-123.2.5.1.2.2 Oxygen Consumption 3-123.2.5.1.2.3 Chemical Releases 3-123.2.5.1.2.4 Cabin Air Heat Leak 3-123.2.5.1.2.5 Cabin Air Cooling 3-133.2.5.1.3 Ionizing Radiation Requirements 3-133.2.5.1.3.1 Instrument Contained or Generated Ionizing Radiation 3-133.2.5.1.3.2 Ionizing Radiation Dose 3-133.2.5.1.3.3 Single Event Effect (SEE) Ionizing Radiation 3-143.2.5.1.4 Additional Environmental Conditions 3-143.2.5.1.5 Pressure Rate of Change 3-163.2.5.2 Acoustic Emission Limits 3-213.2.5.2.1 Continuous Noise Limits 3-213.2.5.2.2 Intermittent Noise Limits 3-213.2.5.3 Instrument Surface Temperature 3-243.2.6 Transportability 3-243.2.6.1 Launch and Landing 3-243.2.7 Operational Interface Requirements 3-253.2.7.1 Mechanical Interface Requirements 3-253.2.7.1.1 Connector Physical Mate 3-253.2.7.2 Electrical Interface Requirements 3-253.2.7.2.1 Electromagnetic Radiation 3-253.2.7.2.1.1 Electromagnetic Compatibility (EMC) 3-253.2.7.2.1.1.1 Electrical Grounding 3-263.2.7.2.1.1.2 Electrical Bonding 3-263.2.7.2.1.2 Electromagnetic Interference 3-273.2.7.2.2 Electrostatic Discharge 3-293.2.7.2.3 Corona 3-293.2.7.2.4 Cable/Wire Design and Control Requirements 3-293.2.7.2.4.1 Wire Derating 3-293.2.7.2.4.2 Exclusive Power Feeds 3-303.2.7.2.5 Loss of Power 3-303.2.7.2.6 Alternating Current Magnetic Fields 3-313.2.7.2.7 Direct Current Magnetic Fields 3-313.2.7.3 Command and Data Handling Interface Requirements 3-313.2.7.3.1 Word/Byte Notations, Types and Data Transmissions 3-313.2.7.3.1.1 Word/Byte Notations 3-313.2.7.3.1.2 Data Types 3-313.2.7.3.2 HRF Software Requirements 3-32

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CONTENTS (Cont'd)

SectionPage3.2.7.3.3 ISS Command and Data Handling Services Through HRF Common

Software Interface 3-333.2.7.4 Fire Protection Interface Requirements 3-333.2.7.4.1 Fire Prevention 3-333.2.7.4.2 Fire Suppression 3-343.2.7.4.2.1 Portable Fire Extinguisher 3-343.2.7.4.2.2 Fire Suppression Access Port Accessibility 3-353.2.7.4.2.3 Fire Suppressant Distribution 3-353.2.7.4.3 Labeling 3-363.2.7.5 Other Interface Requirements 3-363.3 DESIGN AND CONSTRUCTION 3-393.3.1 Materials, Processes, and Parts 3-393.3.1.1 Materials and Processes 3-393.3.1.2 Sharp Edges 3-413.3.1.2.1 Edge and Corner Requirements 3-413.3.1.3 Electrical, Electronic, and Electromechanical Parts Selection 3-453.3.1.3.1 Burn In Screening Tests 3-463.3.2 Nameplates and Product Marking 3-463.3.2.1 Equipment Identification 3-463.3.3 Workmanship 3-473.3.4 Interchangeability 3-473.3.5 Safety Requirements 3-473.3.5.1 Electrical Safety 3-473.3.5.1.1 Mating/Demating of Powered Connectors 3-483.3.5.1.2 Power Switches/Controls 3-483.3.5.1.3 Ground Fault Circuit Interrupters/Portable Equipment DC Sourcing

Voltage 3-483.3.5.1.4 Portable Equipment/Power Cords 3-483.3.6 Human Engineering 3-493.3.6.1 Closures or Covers Design Requirements 3-493.3.6.2 Interior Color 3-493.3.6.2.1 Rack Mounted Equipment 3-493.3.6.2.2 Stowed/Deployable Equipment 3-493.3.6.2.3 Colors for Soft Goods 3-503.3.7 Anthropometry 3-503.3.7.1 Full Size Range Accommodation 3-503.3.8 System Security 3-503.3.9 Design Requirements 3-503.3.9.1 Structural Design Requirements 3-503.3.9.1.1 Crew Induced Load Requirements 3-51

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CONTENTS (Cont'd)

SectionPage3.3.9.1.2 Safety Critical Structures Requirements 3-523.3.9.2 Electrical Power Consuming Equipment Design 3-523.3.9.2.1 Batteries 3-53

4.0 VERIFICATION PROVISIONS 4-14.1 GENERAL 4-14.1.1 Responsibility for Verifications 4-34.2 ACCEPTANCE AND QUALIFICATION TEST REQUIREMENTS 4-34.2.1 Description of Tests 4-74.2.1.1 Thermal Cycle Tests 4-74.2.1.1.1 Qualification Thermal Cycling 4-74.2.1.1.2 Acceptance Thermal Cycling 4-94.2.1.2 Vibration Tests 4-124.2.1.2.1 Qualification for Acceptance Random Vibration Test 4-124.2.1.2.2 Acceptance Random Vibration Test 4-134.2.1.3 Electromagnetic Compatibility Testing 4-144.2.1.4 Functional Testing 4-144.2.1.5 Burn-In 4-154.2.1.6 Flammability 4-154.2.1.7 Offgassing (Toxicity) 4-164.2.1.8 Bench Handling Test 4-164.2.1.9 Other Tests 4-164.2.1.10 Pre-Delivery Acceptance Test 4-174.2.1.11 Science Verification Testing 4-174.3 DOCUMENTATION OF VERIFICATION AND CERTIFICATION

TESTING 4-18

5.0 PREPARATION FOR SHIPMENT 5-15.1 GENERAL 5-15.2 PACKING, HANDLING, AND TRANSPORTATION 5-25.3 PRESERVATION AND PACKING 5-35.4 MARKING FOR SHIPMENT 5-35.5 NASA CRITICAL SPACE ITEM LABEL 5-3

6.0 NOTES 6-16.1 DEFINITIONS 6-1

APPENDIX A CRITICALITY 3 EQUIPMENT PROGRAM REQUIREMENTSA-1

APPENDIX B VERIFICATION AND CERTIFICATION COMPLIANCEMATRIX B-1

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APPENDIX C FUNCTIONAL REQUIREMENTS, HUMAN FACTORS, ANDJHB 8080.5 C-1

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LIST OF TABLES

Table Page

3.1-1 [EXPERIMENT DESIGNATION] EXPERIMENT UNIQUEEQUIPMENT 3-1

3.1-2 [EXPERIMENT DESIGNATION] EXPERIMENT UNIQUEEQUIPMENT SOFTWARE 3-1

3.2.2.1-1 STOWAGE UNIT WEIGHT ALLOWANCE3-3

3.2.2.2.1-1 STOWAGE UNIT VOLUME ALLOWANCE 3-4

3.2.5.1.2.5-1 AIR HEAT LOAD 3-8

3.2.5.1.4-1 ENVIRONMENTAL CONDITIONS ON ISS 3-9

3.2.5.1.5-1 ISS PRESSURE RATE OF CHANGE 3-10

3.2.5.1.5-2 MPLM PRESSURE RATE OF CHANGE 3-11

3.2.5.2-1 CONTINUOUS NOISE LIMITS 3-12

3.3.2.2-1 RS03PL 3-15

3.3.1.2.1-1 LOOSE EQUIPMENT EDGE AND CORNER RADIUSINGREQUIREMENTS 3-23

3.3.5.1.3-1 LET-GO CURRENT PROFILE THRESHOLD VERSUSFREQUENCY 3-27

3.2.5.2.2-1 INTERMITTENT NOISE LIMITS3-13

3.3.9.1.1-1 CREW-INDUCED LOADS 3-30

4.2-1 NON-CRITICAL HARDWARE QUALIFICATION TESTREQUIREMENTS 4-3

4.2-2 NON-CRITICAL HARDWARE ACCEPTANCE TESTREQUIREMENTS 4-4

4.2.1.2.1-1 QUALIFICATION ACCEPTANCE RANDOM VIBRATION TESTLEVELS 4-8

4.2.1.2.2-1 ACCEPTANCE RANDOM VIBRATION WORKMANSHIP TESTLEVELS 4-9

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LIST OF FIGURES

Figure Page3.2.5.1.4-1 Operating Limits of the ISS Atmospheric Total Pressure, Nitrogen,

and Oxygen Partial Pressures 3-10

3.2.5.1.5-1 Manual Fire Suppression System Performance Characteristics 3-11

3.2.7.4.2.2-1 Manual Fire Suppression Hardware Envelope 3-20

3.2.7.4.2.2-2 Closed Volume PFE Nozzle 3-21

4.2.1.1.1-1 Qualification Thermal Cycling 4-6

4.2.1.1.2-1 Acceptance Thermal Cycling 4-7

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ACRONYMS AND ABBREVIATIONS

{Add and delete entries as necessary}

AC Alternating CurrentADP Acceptance Data PackageAPM Attached Pressurized Module

C&DH Command and Data HandlingCAM Centrifuge Accommodation ModuleCCB Configuration Control BoardCFU Colony Forming UnitsCI Cargo IntegrationCOTS Commercial Off-the-Shelf

dB DecibelsDBA Acoustic Decibel LevelDC Direct CurrentDGCS Display and Graphics Commonality StandardsDR Discrepancy Report

EEE Electrical, Electronic, and ElectromechanicalEMC Electromagnetic CompatibilityEPCE Electrical Power Consuming EquipmenESD Electrostatic DischargeEUE Experiment Unique Equipment

FIAR Failure Investigation Analysis ReportFMEA Failure Modes and Effects AnalysisFPD Flight Projects Division

GFCI Ground Fault Circuit InterrupterGPVP Generic Payload Verification PlanGSE Ground Support Equipment

HR Hazard ReportHRF Human Research FacilityHz Hertz

ICD Interface Control DocumentIDD Interface Definition DocumentIMS Inventory Management Systemin inchISPR International Standard Payload RackISS International Space StationITCS Internal Thermal Control System

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ACRONYMS AND ABBREVIATIONS (Cont'd)

JEM Japanese Experiment ModuleJSC Johnson Space Center

KHz Kilohertz

lb poundlbf pounds force

MDM Multiplexer-Demultiplexer Modulemm millimeterMPLM Mini Pressurized Logistics ModuleMSFC Marshall Space Flight Center

N Newton (metric force measurement)NASA National Aeronautics and Space Administration

ORU Orbital Replacement Unit

P/L PayloadPa Pascalpara. paragraphPDA Pre-Delivery AcceptancePFE Portable Fire ExtinguisherPHTR Packaging, Handling, and Transportation RecordsPI Principal InvestigatorPODF Payload Operations Data Filepsi pounds per square inchpsia pounds per square inch absolutePSRP Payload Safety Review Panel

QAVT Qualification for Acceptance Vibration Testing

rms Root Mean SquareRSP Resupply Stowage Platform

SE&I Systems Engineering and Integrationsec secondSPL Sound Pressure LevelSRD System Requirements DocumentSVT Science Verification Testing

TBD To Be DeterminedTPS Task Performance Sheet

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ACRONYMS AND ABBREVIATIONS (Cont'd)

UIP Utility Interface PanelUOP Utility Outlet PanelUSL United States Lab

V VoltsVDS Verification Data SheetVOILA Visuomotor and Orientation Investigations in Long-duration Astronauts

ºC Degrees CelsiusºF Degrees Fahrenheit

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1.0 SCOPE

This specification defines the Human Research Facility (HRF) programrequirements for Visuomotor and Orientation Investigations in Long-durationAstronauts (VOILA)—E085/507. The VOILA consists of Criticality 3Experiment Unique Equipment (EUE) hardware and software that will be used tosupport the HRF. The term “Experiment Unique Equipment,” as used in thisdocument, is defined as hardware designed to support an HRF Programexperiment and not intended for general use.

The primary governing document for the requirements levied in this document isLS-71000, Program Requirements Document for the Human Research Facility.Other requirements are derived from SSP 57200, Human Research Facility - RackOne Hardware Interface Control Document, and interface requirement documentsfor the various items of HRF equipment.

The requirements in Sections 3, 4, and 5 of this document consist of a minimumset of constraints for Criticality 3 EUE hardware and software. Criticality 3 itemsare defined in SSP 30234. Provisions for verification and subsequent use ofCriticality 3 equipment as part of the HRF program are delineated in Section 5 ofLS-71000.

The VOILA Experiment Unique Equipment shall be reviewed through theInternational Space Station (ISS) Payload Safety Review Panel (PSRP) for SafetyCertification and JSC/NT3 Reliability for designation as Criticality 3 hardware.

The HRF Project Office is the controlling authority for this document. The HRFConfiguration Control Board (CCB) or a delegated authority must approve anydeviations from the requirements of this document. Any change in functionalitythat requires equipment designated as Criticality 3 to be used in a manner that isnot consistent with the requirements specified herein and in LS-71000 will requirethat item or items to be reassessed for criticality as well as applicability of thisdocument.

2.0 APPLICABLE DOCUMENTS

The following applicable documents of the exact issue shown herein form a partof this specification to the extent specified herein. If a revision level or date is notcited, the latest version of the document should be used, as of the date the contractis issued.

All specifications, standards, exhibits, drawings or other documents referenced inthis specification are hereby incorporated as cited in the text of this document.

2.1 DOCUMENTS

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Document Number Revision Document Title

TBD TBD HRF Workstation 2 ICD

FED-STD-595 Rev. B12/89

Colors Used in Government Procurement

JSC-SN-C-0005 Rev. C2/89

National Space Transportation SystemContamination Control Requirements

LS-71000 Rev. A1/00

Program Requirements Document for theHuman Research Facility

MIL-STD-1686 Rev. C10/95

Electrostatic Discharge Control Program forProtection of Electrical and ElectronicParts, Assemblies And Equipment(Excluding Electrically Initiated ExplosiveDevices)

MSFC-STD-250 Rev. A10/77

Protective Finishes for Space VehicleStructures and Associated FlightEquipment, General Specification for

NASA TM 102179 6/91 Selection of Wires and Circuit ProtectiveDevices for STS Orbiter Vehicle PayloadElectrical Circuits

NSTS/ISS 13830 Rev. C,Ch. 17/99

Implementation Procedure for NSTSPayloads System Safety Requirements forPayloads Using the Space TransportationSystem

NSTS-1700.7 Rev. B,Ch. 43/97

Safety Policy and Requirements ForPayloads Using the Space TransportationSystem

NSTS-1700.7B

ISS ADDENDUM

12/95 Safety Policy and Requirements ForPayloads Using the International SpaceStation

NSTS/ISS 18798 Rev. B,Ch. 39/97

Interpretations of NSTS/ISS Payload SafetyRequirements

SSP 30233 Rev. E11/95

Space Station Requirements for Materialsand Processes

SSP 30237 Rev. D7/98

Space Station Electromagnetic Emissionand Susceptibility Requirements

SSP 30240 Rev. C6/99

Space Station Grounding Requirements

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Document Number Revision Document Title

SSP 30242 Rev. D,Ch. 26/99

Space Station Cable/Wire Design andControl Requirements for ElectromagneticCompatibility

SSP 30243 Rev. E,Ch. 36/99

Space Station Requirements forElectromagnetic Compatibility

SSP 30245 Rev. D,Ch. 66/99

Space Station Electrical BondingRequirements

SSP 30312 Rev. F11/95

Electrical, Electronic, andElectromechanical (EEE) and MechanicalParts Management and ImplementationPlan International Space Station Program

SSP 30512 Rev. C9/94

Space Station Ionizing Radiation DesignEnvironment

SSP 30573 Rev. A10/94

Space Station Program Fluid Procurementand Use Control Specification

SSP 41175-2 Rev. B6/97

Software Interface Control Document (ICD)Part 1 Station Management and Control toInternational Space Station Book 2, GeneralSoftware Interface Requirements

SSP 50005 Rev. B,Ch. 19/98

International Space Station Flight CrewIntegration Standard (NASA-STD-3000/T)

SSP 50007 Rev. A11/96

Space Station Inventory ManagementSystem Label Specification

SSP 50008 Rev. B7/98

International Space Station Interior ColorScheme

SSP 52005 Rev. B3/99

Payload Flight Equipment Requirementsand Guidelines for Safety-CriticalStructures

SSP 52050 Rev. A11/98

Software Interface Control Document Part1, International Standard Payload Rack toInternational Space Station

SSP 57000 Rev. C12/98

Pressurized Payloads InterfaceRequirements Document

SSP 57001 Rev. A7/99

Pressurized Payloads Hardware InterfaceControl Document Template

2.2 ORDER OF PRECEDENCE

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In the event of a conflict between the text of this specification and references citedherein, the text of this specification takes precedence. Nothing in thisspecification, however, supersedes applicable laws and regulations unless aspecific exemption has been obtained.

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3.0 SYSTEM REQUIREMENTS

3.1 ITEM DEFINITION

The following items of VOILA EUE will be designed and certified under thisrequirements document for use on ISS as a part of the HRF program. HRFhardware used with this experiment is certified under separate documentationwhich is maintained by the appropriate program(s).

Table 3.1-1 lists the equipment items covered by this document.

TABLE 3.1-1. VOILA EXPERIMENT UNIQUE EQUIPMENT

Item Name Part Number QualityFlown

Notes

Head Mounted Display TBD 1 Includes separate interface electronics box

Optical Tracker TBD 2 Includes separate interface electronics box

Inertial Tracker TBD 3 Includes separate interface electronics box

Subject Input Device TBD 1 Joystick input to HRF workstation

Subject Restraint System TBD 1 Passive

Table 3.1-2 lists the software items covered by this document.

TABLE 3.1-2. VOILA EXPERIMENT UNIQUE EQUIPMENT SOFTWARE

Program Name Part Number Notes

Session Manager TBD

Experiment Manager TBD

Data Manager TBD

3.1.1 Experiment Description

3.1.1.1 Experiment Overview

This ISS HRF investigation extends, simplifies, and merges two sensory motorand performance experiments originally developed for the 1998 STS90 Neurolabmission. The two components retain separate numbers (E085/E507) on ISS, butare performed together. The experiments use the HRF Workstation 2 as “sciencekiosk” to perform short (typically 30 minute long) tests to study the role of visual,vestibular, and haptic cues on spatial orientation and motor behavior. Theexperiment utilizes virtual environment generation accessories first developed forthe Neurolab as a tool to study these processes during and after long duration (3-6

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month) orbital flight. Restrained and free-floating subjects wear a wide field ofview, color stereo head mounded display. Tests are based on 1-G paradigms,require little set-up time, and can be selected and performed by an astronaut in anautomated fashion using Session Manager software. Three pre-flight, three inflight, and three post-flight performances of each test are planned on each ISSincrement.

The Specific Objectives are

To determine the effects of microgravity on:

(1) The influence of scene symmetry, rotation, haptic cues, and expectedorientation on static and dynamic self tilt (Virtual Tilting and Tumbling RoomTests); (2) the onset of x-axis illusory linear self-motion without haptic cues(Linear Vection Test); (3) the effect of perceived orientation on visual objectrecognition and shape recognition (Object Recognition Tests); (4) whetherinformation used in grasping remembered objects is stored in head fixed, bodyfixed, or exocentric reference frames (Virtual Grasping Test); and (5) how thetiming of catching movements depends on anticipation of downward acceleration(Virtual Catching Test).

3.1.1.2 Operational Overview

In each session, based on the amount of crewtime available, the WorkstationSession Manager program suggests one or more of 5 different visual perceptiontests and one or more of 4 different visuomotor tasks. Inflight tests are performedin up to 3 possible conditions: quasi-free floating, lightly restrained and/or withconstatnt-force springs (simulated gravity). Pre-and post-flight tests will beconducted in one of three conditions: erect, supine, or with a tilted seat.

Visual PerceptionTest 1: Tilted Room. Subject indicates perceived vertical while viewing a seriesof tilted scenes.Test 2: Tumbling Room. Subject indicates vection magnitude and surface identitywhile viewing rotating scenes.Test 3: Linear Vection. Subject indicates vection onset and magnitude whileviewing a moving corridor scene.Test 4: Figures. Subject indicates which complex 2D figure seems most familiar.Test 5: Shading. Subject indicates which shaded circle seems most convex.

Visuomotor CoordinationTest 6: Grasping. Upright. Subjects align the hand with a object oriented in 3Dspace.Test 7: Grasping. Head Tilt. Subjects repeat Test 6 with 30 head tilt.Test 8: Pointing. Subjects perform rapid point-to-point movements with thedominant hand.Test 9: Interception. Subjects intercept a flying ball with the dominant hand.

Three inflight performances of each test. The first should be during Week 2 (FD8to FD14), the second during Week 5 (FD29 to FD35), and the third during Week

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11 (FD71 to FD77). Depending on crew schedules, it would be highly desirable toschedule one additional performance during Week 1 (FD1 to FD7) and anotherabout 3-4 weeks before the end of the increment (R-21 to R-28). If possible,additional performances every six weeks after Week 11 until as late as possiblewould also be desirable.

3.2 CHARACTERISTICS

3.2.1 Performance Characteristics

3.2.1.1 Functional Performance Characteristics

A. Note: Functional requirements for the VOILA EUE are described inVisuomotor and Orientation Investigations in Long-duration Astronauts—E085/507 Experiment Document (ED), LS-20427. Functional requirementsfor HRF subrack payloads, stowed equipment, and deployed equipment thatmay be used in conjunction with this EUE are described in the individualequipment hardware requirements documents.

B. Equipment provided under this document should, as a minimum, be verifiedto be functionally acceptable for its intended operational lifetime.

C. Upon arrival at Johnson Space Center (JSC), the VOILA shall undergo fullexperiment protocol test and checkout.

D. This testing shall be documented on a Task Performance Sheet (TPS) (JSCForm 1225) per JSC Work Instruction NT1-CWI-001.

E. This testing shall be of sufficient level to demonstrate end-to-end functionalityof the VOILA EUE.

3.2.1.2 Equipment Performance Characteristics

{Specific equipment performance characteristics necessary for the successfulcompletion of the intended experiment should be detailed in this section. As anexample, if an item of measuring equipment associated with the experiment wererequired to measure parameters over a certain range (i.e., 400 millivolts, or 0.2 -100 ml/min, etc.) and have a certain accuracy (i.e., ±0.5% Full Scale, or ±2% ofreading, etc.), these items would be regarded as equipment performancecharacteristics.}

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3.2.2 Physical Characteristics

3.2.2.1 Mass Properties

{Weight requirements for the VOILA are as negotiated with the developer and aredocumented in the ED.}

3.2.2.2 Envelope

{Stowed and deployed envelope requirements for the hardware are as negotiatedwith the developer and are documented in the ED.}

3.2.2.2.1 Stowed Envelope

{If stowed envelope dimensions are critical features of the hardware or if there isa dimensional value which must be met within a given tolerance or which cannotbe exceeded (e.g., for stowage), that dimensional requirement should be specifiedin this section. Otherwise, the requirement for hardware to be measured and itsdimensions documented on a TPS (JSC Form 1225) should be stated in thissection. The tolerance of the measuring system should also be recorded on thisform. As an alternative, the hardware provider may provide the item dimensionsand the measuring system tolerance as part of the data package. Estimatedstowed envelope dimensions should be provided as early in the design process aspossible. Note: This data is to be provided for flight integration purposes.}]

{Table 3.2.2.2.1-1 is provided as a guide.}

TABLE 3.2.2.2.1-1. STOWAGE UNIT VOLUME ALLOWANCE

Stowage Unit Volume Allowance (1) Reference

Middeck Modular StowageLocker

2 ft317.3 in (W) 20.3 in (D) x 10.0 in (H)

NSTS-21000-IDD-MDK,Section 3.4.1

Middeck Standard StowageTray

1.8 ft317.0 in (W) x 20.0 in (D) x 9.5 in (H)

(Top Opening is 14.5 in x 18.6 in)

NSTS-21000-IDD-MDK,Section 3.4.1.1

4 PU Drawer 1.3 ft316.2 in (W) x 23.7 in (D) x 5.9 in (H)

SSP 52000-PAH-ERPSection 4.1.2

SSP 52000-IDD-ERPSection 3.4.4

Resupply Stowage Platform 1 -Stowage System (RSP1-SS)M1 Bag (6 CTBE)M2 Bag (4 CTBE)

M1 Bag (6 CTBE)M2 Bag (4 CTBE)

13 ft335.3 in (W) x 21.0 in (D) x 32.2 in (H)

8 ft335.3 in (W) x 21.0 in (D) x 20.0 in (H)

TBD

(1) The volume allowances and dimensions shown are only approximate. The payloads must meet the height,width, and depth limitations of the Stowage unit as well as the interface requirements for the individualStowage Unit.

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3.2.2.2.2 Deployed Envelope

3.2.2.2.2.1 Hardware Protrusion Limits

3.2.2.2.2.1.1 Permanent Protrusions

Integrated rack payload hardware shall only extend beyond the NationalAeronautics and Space Administration (NASA) International Standard PayloadRack (ISPR) front face Ground Support Equipment (GSE) attachment points asdefined in SSP 41017 and agreed to by ISS in the unique payload ICDs. Payloadhardware extended or attached on-orbit may protrude beyond the face of theNASA ISPR front face GSE attachment points only on an intermittent ortemporary basis. Payload work corridor will be 50 inches x 72 inches, (50 inchesY axis, 72 inches Z axis). (LS-71000, Section 6.4.4.1.1)

3.2.2.2.2.1.2 Intermittent Protrusions

A. Intermittent protrusions are defined as equipment which remains setup in theaisle over a period of days, during which time crew attendance is repeatedlyrequired. Intermittent protrusions shall be limited to 17 inches beyond theplane of the NASA ISPR front face GSE attachment points (except forpayloads manifested in the floor or ceiling locations which are limited to 6inches). (LS-71000, Section 6.4.4.1.2A)

B. Intermittent protrusions shall be easily stowable. (LS-71000, Section6.4.4.1.2B)

3.2.2.2.2.1.3 Temporary Protrusions

Temporary protrusions are defined as equipment which remains set up in the aislefor a period of less than eight hours, during which time crew attendance will benearly continuous. Temporary protrusions shall be limited to 26 inches beyondthe plane of the NASA ISPR front face GSE attachment points. (LS-71000,Section 6.4.4.1.3)

3.2.2.2.2.1.4 Clearance for Crew Restraints and Mobility Aids

Protrusions, intermittent or temporary shall not interfere with crew mobility andtranslation restraints. Any temporary or intermittent protrusions will createadditional rack placement constraints and risks to the microgravity environmentof the payload. (LS-71000, Section 6.4.4.1.4)

3.2.2.2.2.2 Deployed Envelope Dimensions

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{The deployed hardware dimensions must conform to the limitations stated in3.2.2.2.2.1. If other deployed envelope dimensions are critical features of thehardware or if there is a dimensional value which must be met within a giventolerance or which cannot be exceeded, that dimensional requirement should bespecified in this section. Otherwise, hardware should be measured and itsdimensions documented on a TPS (JSC Form 1225). The tolerance of themeasuring system should also be recorded on this form. As an alternative, thehardware provider may provide the item dimensions and the measuring systemtolerance as part of the data package. Estimated deployed envelope dimensionsshould be provided as early in the design process as possible. Note: This data isto be provided for flight integration purposes.}

{If the stowed and deployed envelope dimensions are the same, state that they arethe same in this section and reference Section 3.2.2.2.1 of this document.}

3.2.3 Reliability

This specification applies only to equipment designated as Criticality 3 inaccordance with the criteria stated in LS-71000, Section 3.2.

3.2.3.1 Failure Propagation

The design shall preclude propagation of failures from the payload to theenvironment outside the payload. (NSTS 1700.7B, Section 206)

3.2.4 Maintainability

A. Payload provided unique tools shall meet the requirements of SSP 50005,paragraph 11.2.3. (LS-71000, Section 6.4.4.2.6.3)

B. All Orbital Replacement Units (ORUs) connectors, whether operated by handor tool, shall be designed and placed so they can be mated/demated usingeither hand. (LS-71000, Section 6.4.4.3.1)

C. It shall be possible to mate/demate individual connectors without having toremove or mate/demate connectors on other ORUs or payloads duringmaintenance operations. (LS-71000, Section 6.4.4.3.2B)

D. Electrical connectors and cable installations shall permit disconnection andreconnection without damage to wiring connectors. (LS-71000, Section6.4.4.3.2C)

E. Access to inspect or replace a hardware item (e.g., an ORU) which is plannedto be accessed on a daily or weekly basis shall not require removal of anotherhardware item or more than one access cover. (LS-71000, Section 6.4.4.2.6)

F. Payload containers of liquids or particulate matter shall have built-inequipment/methods for control of vaporization, material overflow, or spills.

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LS-71000, Section 6.4.3.1.2A)

G. The capture elements, including grids, screens, or filter surfaces shall beaccessible for replacement or cleaning without dispersion of the trappedmaterials. (LS-71000, Section 6.4.3.1.2B)

3.2.4.1 Logistics and Maintenance

{ Describe all ORUs for the VOILA. EUE.} TBD

3.2.4.1.1 Payload In-Flight Maintenance

Payloads shall be designed to be maintainable using Space Station provided on-board tools. Available tools on-orbit are defined in the PayloadsAccommodations Handbook. (LS-71000, Section 6.4.10)

3.2.4.1.2 Maintenance Functions

None

3.2.5 Environmental Conditions

3.2.5.1 On-Orbit Environmental Conditions

3.2.5.1.1 On-Orbit Internal Environments

3.2.5.1.1.1 Pressure

The VOILA EUE shall be safe when exposed to pressures of 0 to 104.8 kPa (0 to15.2 psia). (LS-71000, Section 6.3.6.1.1)

3.2.5.1.1.2 Temperature

The VOILA EUE shall be safe when exposed to temperatures of 10° to 46° C (50to 115° F). (LS-71000, Section 6.3.6.1.2)

3.2.5.1.1.3 Humidity

The VOILA EUE shall be designed to not cause condensation when exposed to adewpoint of 4.5° to 15.6° C (40° to 60° F) and a relative humidity of 25% to 75%.(LS-71000, Section 6.3.6.1.3)

3.2.5.1.2 Use of Cabin Atmosphere

3.2.5.1.2.1 Active Air Exchange

LS-71143 - 3/3/00 3-8

Active air exchange with the cabin atmosphere by the VOILA EUE shall belimited to air exchange for specimen metabolic purposes and for massconservation purposes. (LS-71000, Section 6.3.6.2.1)

3.2.5.1.2.2 Oxygen Consumption

Not applicable to VOILA.

3.2.5.1.2.3 Chemical Releases

Chemical releases to the cabin air shall be in accordance with paragraphs 209.1aand 209.1b in NSTS 1700.7, ISS Addendum. (LS-71000, Section 6.3.6.2.3)

3.2.5.1.2.4 Cabin Air Heat Leak

Cabin air heat rejection is defined by the ISS program in terms of ISS modulesonly. No sub-allocation has been made for integrated racks or EUE. VOILAEUE maximum cabin air heat rejection must be documented in the VOILA EUEICD. (LS-71000, Section 6.3.4.2)

3.2.5.1.2.5 Cabin Air Cooling

The VOILA EUE air heat load absorption shall be no greater than the maximumvalues listed in Table 3.2.5.1.2.5-1, with linear interpolation to ambienttemperatures between the specified values. (LS-71000, Section 6.3.4.3)

TABLE 3.2.5.1.2.5-1. AIR HEAT LOAD

Ambient Temperature Max Heat Load

15.5° C (60° F) 68 W

49° C (120° F) 140 W

3.2.5.1.3 Ionizing Radiation Requirements

3.2.5.1.3.1 Instrument Contained or Generated Ionizing Radiation

Not applicable to VOILA

3.2.5.1.3.2 Ionizing Radiation Dose

EUE should expect a total dose (including trapped protons and electrons) of 30Rads (Si) per year of ionizing radiation. A review of the dose estimates in the ISS

LS-71143 - 3/3/00 3-9

(SAIC-TN-9550) may show ionizing radiation exposure to be different than 30Rads (Si) per year, if the intended location of the rack in the ISS is known.(LS-71000, Section 6.3.6.3.2)

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3.2.5.1.3.3 Single Event Effect (SEE) Ionizing Radiation

The VOILA EUE shall be designed not to produce an unsafe condition or one thatcould cause damage to equipment external to the VOILA EUE as a result ofexposure to SEE ionizing radiation assuming exposure levels specified in SSP30512, paragraph 3.2.1, with a shielding thickness of 25.4 mm (1000 mils). (LS-71000, Section 6.3.6.3.3)

3.2.5.1.4 Additional Environmental Conditions

TABLE 3.2.5.1.4-1. ENVIRONMENTAL CONDITIONS ON ISS

Environmental Condition ValueAtmospheric Conditions

Pressure Extremes 0 to 104.8 kPa (0 to 15.2 psia)Normal operating pressure See Figure 3.2.5.1.4-1Oxygen partial pressure See Figure 3.2.5.1.4-1Nitrogen partial pressure See Figure 3.2.5.1.4-1Dewpoint 4.4 to 15.6 °C (40 to 60 °F)Percent relative humidity 25 to 75Carbon dioxide partial pressure duringnormal operations with 6 crewmembersplus animals

24-hr average exposure 5.3 mm HgPeak exposure 7.6 mm Hg

Carbon dioxide partial pressure duringcrew changeout with 11 crewmembersplus animals

24-hr average exposure 7.6 mm HgPeak exposure 10 mm Hg

Cabin air temperature in United StatesLab (USL), Japanese Experiment Module(JEM), Attached Pressurized Module(APM), and Centrifuge AccommodationModule (CAM)

17 to 28 °C (63 to 82 °F)

Cabin air temperature in Node 1 17 to 31 °C (63 to 87 °F)Air velocity 0.051 to 2.03 m/s (10 to 40 ft/min)

Airborne microbes Less than 1000 Colony Forming Units (CFU)/m3

Atmosphere particulate level Average less than 1000,000 particles/ft3 for particles lessthan 0.5 microns in size

MPLM Air Temperatures Active and Passive FlightsExtremes for all phases of flight 10 to 46 °C (50 to 114.8 °F)

Thermal ConditionsModule wall temperature 13 °C to 43 °C (55 °F to 109 °F)Other integrated payload racks Front surface less than 37 °C (97 °F)

Microgravity TBDGeneral Illumination 108 Lux (10 fc) measured 30 inches from the floor in the

center of the aisle

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O2 Partial Pressure (psia)

To

talP

ress

ure

(psi

a)

2.83 3.5915.5

15.0

14.5

14.0

13.52.0 2.5 3.0 3.5 4.0

Maximum N2Partial Pressure

(11.6 psia)

O2 PartialPressure

Control Band

Total PressureControl Band

FlammabilityLimit

(24.1% O2)Low Logistics TotalPressure Contingency

Figure 3.2.5.1.4-1. Operating Limits of the ISS Atmospheric Total Pressure, Nitrogen, andOxygen Partial Pressures

3.2.5.1.5 Pressure Rate of Change

A. The VOILA EUE shall maintain positive margins of safety for the on-orbitdepress/repress rates in Table 3.2.5.1.5-1. (LS-71000, Section 6.3.1.2B)

TABLE 3.2.5.1.5-1. ISS PRESSURE RATE OF CHANGE

Depressurization 878 Pa/sec (7.64 psi/minute)

Repressurization 230 Pa/sec (2.0 psi/minute)

B. Not applicable to VOILA EUE.

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C. EUE shall maintain positive margins of safety for maximum depressurizationand repressurization rates for the carrier(s) in which it will be transported.(LS-71000, Section 6.3.1.2A)

D. EUE that have Portable Fire Extinguisher (PFE) access ports shall maintainpositive margins of safety when exposed to the PFE discharge rate given inFigure 3.2.5.1.5-1. (LS-71000, Section 6.3.1.2C)

Figure 3.2.5.1.5-1. Manual Fire Suppression System Performance Characteristics

MASS DISCHARGED IN 10 SECONDS = 3.424 LBMMASS DISCHARGED IN 45 SECONDS = 5.646 LBM

MA

SS

(LB

S)

ELAPSED TIME (SECONDS)

7

6

5

4

3

2

1

0-10 0 10 20 30 40 50 60 70

LS-71143 - 3/3/00 3-13

3.2.5.2 Acoustic Emission Limits

3.2.5.2.1 Continuous Noise Limits

VOILA EUE continuous acoustical emissions shall individually comply with theacoustic requirements (NC-40 equivalent) in Table 3.2.5.2-1. (LS-71000, Section6.4.3.3.1C)

TABLE 3.2.5.2-1. CONTINUOUS NOISE LIMITS

Rack Noise Limits Measured at 0.6 Meters Distance From the Test Article

Frequency Band(Hz)

Integrated Rack Sound Pressure Level(SPL)

63 64

125 56

250 50

500 45

1000 41

2000 39

4000 38

8000 37

3.2.5.2.2 Intermittent Noise Limits

A. The Integrated rack (including any supporting adjunct active portableequipment operated outside the integrated rack that is within or interfacingwith the crew habitable volume) Intermittent Noise Source (See Glossary ofTerms) shall not exceed the Total Rack A-weighted SPL Limits during theMaximum Rack Noise Duration as specified in Table 3.2.5.2.2-1 when theequipment is operating in the loudest expected configuration and mode ofoperation that can occur on orbit under any planned operations. (LS-71000,Section 6.4.3.3.2A)

Note: These acoustic requirements do not apply during failure or maintenanceoperations.

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TABLE 3.2.5.2.2-1. INTERMITTENT NOISE LIMITS

Rack Noise Limits Measured

At 0.6 Meters Distance From The Test Article

Maximum Rack Noise Duration Total Rack A - Weighted SPL (DBA)

8 Hours 49

7 Hours 50

6 Hours 51

5 Hours 52

4 Hours 54

3 Hours 57

2 Hours 60

1 Hour 65

30 Minutes 69

15 Minutes 72

5 Minutes 76

2 Minutes 78

1 Minute 79

Not Allowed 80

B. The Rack Noise Duration is the total time that the rack produces intermittentnoise above the NC-40 limit during a 24 hour time period. This duration isthe governing factor in determining the allowable Intermittent Noise Limits.Regardless of the number of separate sources and varying durations within arack, this cumulative duration shall be used to determine the A-weighted SPLlimit in column B. (LS-71000, Section 6.4.3.3.2B)

3.2.5.3 Instrument Surface Temperature

The VOILA EUE shall be designed such that the average surface temperature isless than 37° C (98.6° F) with a maximum temperature limit not to exceed 45° C(113° F). (LS-71000, Section 6.3.4.1)

3.2.6 Transportability

3.2.6.1 Launch and Landing

The VOILA EUE shall be transportable to and from orbit. Equipment carried inthe Shuttle mid-deck lockers shall be transportable in the Shuttle mid-deck locker to and from orbit, as specified in NSTS-21000-IDD-MDK.

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3.2.7 Operational Interface Requirements

{Provide a block diagram and describe all interfaces with the HRF Rack and/orISS and/or Shuttle in these sections.}

3.2.7.1 Mechanical Interface Requirements

3.2.7.1.1 Connector Physical Mate

Where required, the VOILA EUE shall physically mate with the Utility InterfacePanel (UIP), Utility Outlet Panel (UOP), and Fluid Services connectors intendedto be used by the payload as listed in Table 3.1.1.6.1-1 of SSP 57000.

{Describe the [name of equipment] mechanical interface requirements with theHRF Rack, HRF Rack Equipment, ISS and/or Shuttle in this section. ReferenceSSP 57000, SSP 57001, Shuttle interface documentation, and HRF equipmentICDs for specific interface data.}

3.2.7.2 Electrical Interface Requirements

{Describe the EUE electrical interface requirements with the HRF Rack, HRFRack Equipment, ISS and/or Shuttle in this section. Reference SSP 57000, SSP57001, Shuttle interface documentation, and HRF equipment ICDs for specificinterface data.}

3.2.7.2.1 Electromagnetic Radiation

3.2.7.2.1.1 Electromagnetic Compatibility (EMC)

The VOILA EUE shall meet the payload provider applicable requirements of SSP30243, paragraphs 3.1, 3.5, and 3.6.2. (LS-71000, Section 6.3.2.4)

3.2.7.2.1.1.1 Electrical Grounding

The VOILA EUE shall meet all requirements specified in Section 3 of SSP30240. (LS-71000, Section 6.3.2.4.1)

3.2.7.2.1.1.2 Electrical Bonding

Electrical bonding of the VOILA EUE shall be in accordance with Class [bondingclass] SSP 30245 and NSTS 1700.7, ISS Addendum, Sections 213 and 220. (LS-71000, Section 6.3.2.4.2) {The hardware provider in conjunction with HRFSE&I will analyze the hardware application and determine the applicablebonding class per Section 3.2.1 of SSP 30245.}

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3.2.7.2.1.2 Electromagnetic Interference

{ The need to perform susceptibility tests is determined upon initiation of theVOILA project. If susceptibility tests are performed, the levels in B and C belowmay be applied to Criticality 3 equipment for radiated susceptibility.}

A. The VOILA shall meet all EMI requirements of SSP 30237.(LS-71000, Section 6.3.2.4.4)

B. Note: The alternative use of RS03 stated below applies to radiatedsusceptibility requirements only. (LS-71000, Section 6.3.2.4.4)

C. Alternately, the payload Electrical Power Consuming Equipment (EPCE) maychoose to accept a minimal increase of EMI risk with a somewhat lessstringent Electric Field Radiated Susceptibility (RS03) requirement onequipment considered to be non-safety critical to the vehicle and crew. Thetailored RS03 requirement, shown below, will hereafter be denoted RS03PL.(LS-71000, Section 6.3.2.4.4)

TABLE 3.3.2.2-1. RS03PL

FREQUENCY RS03PL LIMIT (V/m)

14 kHz - 400 MHz 5

400 MHz - 450 MHz 30

450 MHz - 1 GHz 5

1 GHz - 5 GHz 25

5 GHz - 6 GHz 60

6 GHz - 10 GHz 20

13.7 GHz - 15.2 GHz 25

D. Comments: The less stringent RS03PL limit was developed to envelope theelectric fields generated by ISS transmitters and ground-based radars tasked toperform space surveillance and tracking. Ground-based radars that are nottasked to track the ISS and search radars that could momentarily sweep overthe ISS are not enveloped by the relaxed RS03PL. For most scientificpayloads, the minimal increase of EMI risk for the reduced limits isacceptable. The RS03PL limit does not account for module electric fieldshielding effectiveness that could theoretically reduce the limits even more.Although shielding effectiveness exists, it is highly dependent on the EPCElocation within the module with respect to ISS windows.

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3.2.7.2.2 Electrostatic Discharge

A. Unpowered VOILA EUE EPCE shall not be damaged by ElectrostaticDischarge (ESD) equal to or less than 4000 V to the case or any pin onexternal connectors. (LS-71000, Section 6.3.2.5)

B. VOILA EUE EPCE that may be damaged by ESD between 4000 V and15,000 V shall have a label affixed to the case in a location clearly visible inthe installed position. (LS-71000, Section 6.3.2.5)

C. Labeling of VOILA EUE EPCE susceptible to ESD up to 15,000 V shall be inaccordance with MIL-STD-1686. (LS-71000, Section 6.3.2.5)

D. Note: These voltages are the result of charges that may be accumulated anddischarged from ground personnel or crewmembers during equipmentinstallation or removal. (LS-71000, Section 6.3.2.5)

3.2.7.2.3 Corona

The VOILA EUE shall be designed to preclude damaging or destructive corona inits operating environment. Guidance for meeting the corona requirement is foundin MSFC-STD-531, High Voltage Design Criteria. (LS-71000, Section 6.3.2.8)

3.2.7.2.4 Cable/Wire Design and Control Requirements

The VOILA EUE shall meet all Cable and Wire requirements of SSP 30242. (LS-71000, Section 6.3.2.4.3)

3.2.7.2.4.1 Wire Derating

A. Wire derating for wire/cable between EUE and the UOP shall be inaccordance with SSP 30312. (LS-71000, Section 6.3.2.1A)

B. Derating criteria for EUE connected to payload rack power outlets shall be perNASA Technical Memo (TM) 102179 as interpreted by NSTS 18798, TA-92-038. (LS-71000, Section 6.3.2.1B)

3.2.7.2.4.2 Exclusive Power Feeds

Cabling shall not occur between Interface C connected EPCE with Interface B;and/or Interface B with Interface C. (LS-71000, Section 6.3.2.2)

3.2.7.2.5 Loss of Power

The VOILA EUE shall fail safe in the event of a total or partial loss of power,regardless of the availability of Auxiliary power in accordance with NSTS1700.7, ISS Addendum. (LS-71000, Section 6.3.2.3)

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3.2.7.2.6 Alternating Current Magnetic Fields

The generated Alternating Current (AC) magnetic fields, measured at a distanceof 7 centimeters (cm) from the generating equipment, shall not exceed 140 dBabove 1 picotesla for frequencies ranging from 30 Hz to 2 KHz, then falling 40dB per decade to 50 KHz. (LS-71000, Section 6.3.2.6)

3.2.7.2.7 Direct Current Magnetic Fields

The generated Direct Current (DC) magnetic fields shall not exceed 170 dBpicotesla at a distance of 7 cm from the generating equipment. This applies toelectromagnetic and permanent magnetic devices. (LS-71000, Section 6.3.2.7)

3.2.7.3 Command and Data Handling Interface Requirements

The following requirements are defined for compatibility with HRF CommonSoftware on the HRF portable computer.

3.2.7.3.1 Word/Byte Notations, Types and Data Transmissions

3.2.7.3.1.1 Word/Byte Notations

HRF rack independent instruments shall use the word/byte notations as specifiedin paragraph 3.1.1, Notations in SSP 52050. (LS-71000, Section 6.3.3.1.1)

3.2.7.3.1.2 Data Types

HRF rack independent instruments shall use the data types as specified inparagraph 3.2.1 and subsections, Data Formats in SSP 52050. (LS-71000, Section6.3.3.1.2)

3.2.7.3.2 HRF Software Requirements

A. File pathnames required for proper execution of the software shall be readfrom a configuration file rather than “hard coded” in the software. (LS-71000,Section 6.3.3.2A)

B. The rack independent instrument software shall execute in the environmentdescribed in the host system IDD. (Workstation, Laptop, Common Software)(LS-71000, Section 6.3.3.2B)

C. The Rack independent instruments software executable shall generateconsistent results given the same initialization data. (LS-71000, Section6.3.3.2C)

LS-71143 - 3/3/00 3-19

D. User interface software shall comply with the Display and GraphicsCommonality Standards (DGCS) (http://139.169.159.8/idags/dgcs.html) andthe International Space Station Operations United States Payload OperationsData File Payload Display Implementation Plan. (LS-71000, Section 6.3.3.2D

E. Real-time data shall be formatted in accordance with the Life Sciences DataSystem (LSDS) Format. (LS-71000, Section 6.3.3.2E)

3.2.7.3.3 ISS Command and Data Handling Services Through HRF Common SoftwareInterface

Rack independent instruments obtaining HRF rack and Payload Multiplexer-Demultiplexer Module (MDM) services (e.g., ancillary data requests, file transfer,report health and status, etc.) through the HRF Common Software shall requestservices in accordance with LS-71062-8, Interface Definition Document for theHuman Research Facility Common Software. (LS-71000, Section 6.3.3.3)

3.2.7.4 Fire Protection Interface Requirements

Fire detection requirements for instruments operated outside of rack volumes havenot been defined by ISS. Fire detection methodology for instruments operatedoutside of rack volumes must be approved by the PSRP. Fire protectionrequirements in this section apply to all instruments. Fire suppressionrequirements in this section apply for instruments operated outside of the rackvolume that have forced air flow. (LS-71000, Section 6.3.7)

3.2.7.4.1 Fire Prevention

The VOILA EUE shall meet the fire prevention requirements specified in NSTS1700.7B, ISS Addendum, paragraph 220.10a. (LS-71000, Section 6.3.7.1)

3.2.7.4.2 Fire Suppression

3.2.7.4.2.1 Portable Fire Extinguisher

A. VOILA EUE instruments with forced air flow that have a panel thickness lessthan or equal to 3.175 mm (0.125 inch) and contain a potential fire sourceshall provide a PFE access port that is between 12.7 mm (0.5 inch) and 25.4mm (1.0 inch) in diameter. PFE discharge characteristics are specified inFigure 3.2.5.1.5-1. (LS-71000, Section 6.3.7.2.1A)

B. VOILA EUE instruments with forced air flow that have a panel thicknessgreater than 3.175 mm (0.125 inch) and contain a potential fire source shallprovide a PFE access port that is 25.4 mm (1.0 inch) in diameter. PFEdischarge characteristics are specified in Figure 3.2.5.1.5-1. (LS-71000,Section 6.3.7.2.1B)

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Note 1: The final determination of whether or not a payload volumecontains a potential fire source and requires a PFE access port willbe presented to and approved by the PSRP during the phasedsafety reviews. (LS-71000, Section 6.3.7.2.1 Note 1)

Note 2: The ISS PFE has an “open cabin” diffuser nozzle which will beused to surround fire events that are not in an enclosed volumewith suppressant. (LS-71000, Section 6.3.7.2.1 Note 2)

Note 3: Internal volumes are volumes which are presented to and approvedby the PSRP as sealed containers and do not require PFE accessports. (LS-71000, Section 6.3.7.2.1 Note 3)

3.2.7.4.2.2 Fire Suppression Access Port Accessibility

VOILA EUE requiring an access port shall have a front face designed toaccommodate the PFE nozzle and bottle specified in Figures 3.2.7.4.2.2-1 and3.2.7.4.2.2-2 so the PFE nozzle can interface to the PFE port. (LS-71000, Section6.3.7.2.2)

3.2.7.4.2.3 Fire Suppressant Distribution

The internal layout of the VOILA EUE shall allow ISS PFE fire suppressant to bedistributed to the entire volume that PFE Access Port serves, lowering the Oxygenconcentration to or below 10.5% by volume at any point within the enclosurewithin one minute. (LS-71000, Section 6.3.7.2.3)

Note: The position of VOILA EUE components near the PFE Access Portshould not prevent fire suppressant to be discharged into the volume thePFE Access Port serves. PFE discharge characteristics are specified inFigure 3.2.5.1.5-1 and PFE closed volume nozzle dimensions arespecified in Figure 3.2.7.4.2.2-2. (LS-71000, Section 6.3.7.2.3 Note)

3.2.7.4.3 Labeling

HRF VOILA EUE items requiring an access port shall label the PFE access portwith a SDD32100397-002 “Fire Hole Decal” specified in JSC 27260, “DecalProcess Document and Catalog.” (LS-71000, Section 6.3.7.3)

3.2.7.5 Other Interface Requirements

Not applicable to VOILA.

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¯ 10.26(206.6)

NOTE: Measurement from PFE centerline to point B with theClosed Cabin Nozzle attached is approximately 14.59 inches (370.6 mm).

B

B

Attaches to Interface A

Open Cabin Area Nozzle

Closed Volume Nozzle

0.463(11.7)

12.68 ± 0.10(322.1 ± 2.5)

Closed Volume Nozzledimensions specified inFigure 3.2.7.4.2.2-2

(Interface A)

2.375(60.3)

PFE

19.10(485.1)15.65

(397.5)

Figure 3.2.7.4.2.2-1. Manual Fire Suppression Hardware Envelope

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C B L ∅0 .0 5 9 h o l e s

S e c t i o n A -A

A

A

0 .4 6 3

0. 0 8

∅0 . 0 8 2

6 0°

0 .6 2 5 0 .3 7 5

NOTE: Linear dimensions are in inches, angular dimensions are in degrees.

Figure 3.2.7.4.2.2-2. Closed Volume PFE Nozzle

3.3 DESIGN AND CONSTRUCTION

3.3.1 Materials, Processes, and Parts

3.3.1.1 Materials and Processes

A. The VOILA EUE shall use materials and parts that meet the materialsrequirements specified in NSTS 1700.7, ISS Addendum, Section 209.(LS-71000, Section 6.3.8.1)

B. Commercial-Off the Shelf (COTS) parts used in the VOILA EUE shall meetthe materials requirements specified in NSTS 1700.7, ISS Addendum, Section209. (LS-71000, Section 6.3.8.2)

C. Internal and exterior surfaces of the VOILA EUE shall conform to VisiblyClean -Sensitive (VC-S) requirements as specified in SN-C-0005. (LS-71000,Section 6.3.8.3)

D. Materials used for exposed interior surfaces shall be selected to precludeparticulate and microbial contamination and shall be smooth, solid, and non-porous. (LS-71000, Section 6.4.3.1.4)

E. HRF EUE instruments that are intended to remain on-orbit for more than oneyear shall use fungus resistant materials according to the requirementsspecified in SSP 30233, paragraph 4.2.10. (LS-71000, Section 6.3.8.4)

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3.3.1.2 Sharp Edges

The VOILA EUE design within a pressurized module shall protect crewmembersfrom sharp edges and corners during all crew operations in accordance with SSP50005, Section 6.3.3 as listed in Section 3.3.1.2.1 of this document. (LS-71000,Section 6.4.9.2)

3.3.1.2.1 Edge and Corner Requirements

A. Exposed Edge Requirements for Facilities and Mounted Hardware

(1) Exposed edges 6.4 mm (0.25 in) thick or greater shall be rounded tominimum radius of 3.0 mm (0.12 in). (SSP 50005, Section 6.3.3.1A)

(2) Exposed edges 3.0 - 6.4 mm (0.12 to 0.25 in) thick or greater shall berounded to minimum radius of 1.5 mm (0.06 in). (SSP 50005, Section6.3.3.1B)

(3) Exposed edges 0.5 - 3.0 mm (0.02 to 0.12 in) thick or greater shall berounded to a full radius. (SSP 50005, Section 6.3.3.1C)

(4) The edges of thin sheets less than 0.5 mm (0.02 in) thick shall be rolled orcurled. (SSP 50005, Section 6.3.3.1D)

B. Exposed Corner Requirements for Facilities and Mounted Hardware

(1) Exposed corners of materials less than 25 mm (1.0 in) thick shall berounded to a minimum radius of 13 mm (0.5 in). (SSP 50005, Section6.3.3.2A)

(2) Exposed corners of materials that exceed 25 mm (1.0 in) thick shall berounded to a radius of 13 mm (0.5 in). (SSP 50005, Section 6.3.3.2B)

C. Protective Covers for Portable Equipment - Portable equipment which doesnot meet the corner and edge requirements of A and B above shall be coveredor shielded when not in use. (SSP 50005, Section 6.3.3.3)

D. Holes - Holes that are round or slotted in the range of 10.0 to 25.0 mm (0.4 to 1.0in) shall be covered. (LS-71000, Section 6.4.9.3, SSP 50005, Section 6.3.3.4)

E. Latches - Latches that pivot, retract, or flex so that a gap of less than 35 mm(1.4 in) exists shall be designed to prevent entrapment of a crewmember’sappendage. (LS-71000, Section 6.4.9.4, SSP 50005, Section 6.3.3.5)

F. Screws and Bolts - Threaded ends of screws and bolts accessible by the crewand extending more than 3.0 mm (0.12 in) shall be capped to protect againstsharp threads. (LS-71000, Section 6.4.9.5, SSP 50005, Section 6.3.3.6)

LS-71143 - 3/3/00 3-24

G. Securing Pins - Securing pins in handrails shall be designed to prevent theirinadvertently backing out above the handhold surface. (LS-71000, Section6.4.9.6, SSP 50005, Section 6.3.3.7)

H. Levers, Cranks, Hooks, and Controls - Levers, cranks, hooks, and controlsshall not be located where they can pinch, snag, or cut the crewmembers ortheir clothing. (LS-71000, Section 6.4.9.7, SSP 50005, Section 6.3.3.8)

I. Burrs - Exposed surfaces shall be free of burrs. (LS-71000, Section 6.4.9.8,SSP 50005, Section 6.3.3.9)

J. Locking Wires - Safety wires shall not be used on fasteners which must beunfastened for on-orbit removal or replacement. (LS-71000, Section 6.4.9.9A)

K. Locking Wires - All fracture-critical fasteners as defined in SSP 52005(paragraph 5.6, Fastener Requirements, and Appendix B, Glossary of Terms),which must be unfastened for on-orbit removal or replacement, shall be safetycabled or cotterpinned. (LS-71000, Section 6.4.9.9B)

L. Locking - Threaded fasteners shall incorporate features that allow them to belocked so they will not unthread without using a tool. (SSP 50005, Sections6.3.3.10 and 11.9.3.3I)

M. Loose Equipment - Loose equipment edge and corner radiusing shall be perTable 3.3.1.2.1-1 (SSP 50005, Section 6.3.3.11)

TABLE 3.3.1.2.1-1. LOOSE EQUIPMENT EDGE AND CORNERRADIUSING REQUIREMENTS

(METRIC)

Mass (Kg) Edge Radius (mm) Corner Radius (mm)

0.0 to 0.25 0.3 0.5

0.25 to 0.5 0.8 1.5

0.5 to 3.0 1.5 3.5

3.0 to 15.0 3.5 7.0

15.0 to 50.0 3.5 13.0

(STANDARD)

Mass (lb) Edge Radius (in) Corner Radius (in)

0.0 to 0.5 0.01 0.02

0.5 to 1.1 0.03 0.06

1.1 to 6.6 0.06 0.14

6.6 to 33.0 0.14 0.3

33.0 to 110.0 0.14 0.5

LS-71143 - 3/3/00 3-25

3.3.1.3 Electrical, Electronic, and Electromechanical Parts Selection

A. As a guide, parts should be controlled in accordance with:

(1) NHB 5300.4(1F), “Electrical, Electronic, and Electromechanical (EEE)Parts Management and Control Requirements for NASA Space FlightPrograms.”

(2)SSP 30312, “Electrical, Electronic, and Electromechanical (EEE) andMechanical Parts Management and Implementation Plan for Space StationProgram.”

B. As a guide, part selection should be in accordance with:

(1) SSP-30423, “Space Station Approved Electrical, Electronic, andElectromechanical (EEE) Parts List.”

(2) SSQ-25002, “Supplemental List of Qualified Electrical, Electronic,Electromechanical (EEE) Parts, Manufacturers, and Laboratories(QEPM&L).”

(3) Semiconductors shall be JANTXV in accordance with MIL-S-19500,“General Specifications for Semiconductor Devices.” Diodes shall have ametallurgical bond. Passive parts shall be at least the second highest levelof appropriate Military Established Reliability (MIL-ER).

(4) SSP-30512C, “Space Station Ionizing Radiation Design Environment.”

C. Where no alternative is available, nonmilitary parts, components, andsubassemblies may be used, but screening of these items shall beaccomplished through burn-in as described in Section 3.3.1.3.1 of thisdocument. Screening shall be completed (100%) on all flight hardware(units).

3.3.1.3.1 Burn In Screening Tests

A. Burn-In screening shall be performed on all flight units where nonmilitaryparts, components, or subassemblies are used. The burn-in test may beaccomplished at the component or assembly level, and is specified as:

� 72 hrs continuously at room ambient temperature while functioning

� 96 hrs continuously at a specified controlled temperature whilefunctioning.

B. Full functional tests shall be performed on the experiment hardware beforeand after the burn-in test. Controlled temperature is defined as 15 °C belowthe maximum rating of the device with the lowest temperature rating in the

LS-71143 - 3/3/00 3-26

article under test. (LS-71000, Section 5.4.1.1.10)

3.3.2 Nameplates and Product Marking

3.3.2.1 Equipment Identification

Integrated racks, all (installed in the rack or separately) sub-rack elements, looseequipment, stowage trays, consumables, ORUs, crew accessible connectors andcables, switches, indicators, and controls shall be labeled. Labels are markings ofany form [including Inventory Management System (IMS) bar codes] such asdecals and placards, which can be adhered, “silk screened,” engraved, orotherwise applied directly onto the hardware. Appendix C of SSP 57000Cprovides instructions for label and decal design and approval. (LS-71000, Section6.4.7) {Labels may be manufactured under the direction or JSC Flight ProjectsDivision (FPD). Labels not manufactured under the direction of JSC FPD, mustbe inspected and approved as meeting the requirements in Appendix C of SSP57000C by JSC FPD. The formal approval process takes about 10 days once acomplete drawing set is received by FPD. Pre-release drawings should besupplied to FPD as early in the design phase as practical, so that recommendedchanges can be incorporated into the final design prior to final formal approval.}

3.3.3 Workmanship

The P/L developer shall use workmanship standards agreed to by NASA(JSC/NT3). The P/L developer may use NASA preferred standards located athttp://standards.nasa.gov

3.3.4 Interchangeability

Parts with the same part number must be interchangeable for maintenance. 3.3.5 Safety Requirements

{The VOILA EUE must meet the applicable requirements of NSTS 1700.7, NSTS1700.7 ISS Addendum, NSTS/ISS 18798, NSTS/ISS 13830, and KHB 1700.7.Applicability of the requirements is determined by working with the Safetyrepresentative assigned to this hardware.}

3.3.5.1 Electrical Safety

EUE shall meet the electrical safety requirements as defined in NSTS 1700.7, ISSAddendum. {Applicability and closure of these requirements is determined byworking with the Safety representative assigned to this hardware.} (LS-71000,Section 6.3.2.10)

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3.3.5.1.1 Mating/Demating of Powered Connectors

A. The VOILA EUE shall comply with the requirements for mating/demating ofpowered connectors specified in NSTS 18798, MA2-97-093. (LS-71000,Section 6.3.2.10.1)

B. Note: The HRF rack or UOP can provide one verifiable upstream inhibitwhich removes voltage from the UIP and UOP connectors. The moduledesign will provide the verification of the inhibit status at the time the inhibitis inserted. (Derived from LS-71000, Section 6.3.2.10.1)

3.3.5.1.2 Power Switches/Controls

A. Switches/controls performing on/off power functions for the VOILA EUEshall open (dead-face) all supply circuit conductors except the power returnand the equipment grounding conductor while in the power-off position. (LS-71000, Section 6.3.2.10.3A)

B. Power-off markings and/or indications shall be used only if all parts, with theexception of overcur rent devices and associated EMI filters, are disconnectedfrom the supply circuit. (LS-71000, Section 6.3.2.10.3B)

C. Standby, charging, or other descriptive nomenclature shall be used to indicatethat the supply circuit is not completely disconnected for this power condition.(LS-71000, Section 6.3.2.10.3C)

3.3.5.1.3 Ground Fault Circuit Interrupters/Portable Equipment DC Sourcing Voltage

Not applicable to VOILA.

3.3.5.1.4 Portable Equipment/Power Cords

Not applicable to VOILA.

3.3.6 Human Engineering

3.3.6.1 Closures or Covers Design Requirements

A. Closures or covers shall be provided for any area of the payload that is notdesigned for routine cleaning. (LS-71000, Section 6.4.3.1.1)

B. Note: As a goal, SSP 50005, Section 11.4.3 may be used as guidelines for thedesign of closures and covers on equipment housing.

3.3.6.2 Interior Color

LS-71143 - 3/3/00 3-28

3.3.6.2.1 Rack Mounted Equipment

Not applicable to VOILA.

3.3.6.2.2 Stowed/Deployable Equipment

The colors and finishes for stowed and deployable equipment, even if it isnormally attached to the rack during use shall be as specified below:

A. COTS equipment that is not repackaged by HRF engineers shall be finished as

delivered by the manufacturer. (LS-71000, Section 6.4.3.5.2A)

B. Items that are repackaged by HRF engineers shall be finished using anodicfilm per MIL-A-8625, Type II, Class 2, Dyed Turquoise. Reference FED-STD-595, Color Specification 15187. (LS-71000, Section 6.4.3.5.2B)

3.3.6.2.3 Colors for Soft Goods

Human factors engineering will provide guidance in the appropriate colors forsoft goods, in cooperation with the lead engineers, who will provide data on theavailable color choices for the specified materials. (LS-71000, Section 6.4.3.5.3)

3.3.7 Anthropometry

3.3.7.1 Full Size Range Accommodation

A. All payload workstations and hardware having crew nominal operations andplanned maintenance shall be sized to meet the functional reach limits for the5th percentile Japanese female and yet shall not constrict or confine the bodyenvelope for the 95th percentile American male as specified in SSP 50005,Section 3. (LS-71000, Section 6.4.2.3)

B. COTS equipment shall be as delivered by the manufacturer and is exemptedfrom this requirement.

C. {Include any special anthropometric requirements for this hardware} - TBD 3.3.8 System Security

Not applicable to VOILA.

3.3.9 Design Requirements

3.3.9.1 Structural Design Requirements

A. EUE shall maintain positive margins of safety for launch and landing loading

LS-71143 - 3/3/00 3-29

conditions for the carrier(s) in which it will be transported. (Reference Section3.2.6.2, this document) (LS-71000, Section 6.3.1.3A)

B. EUE shall provide positive margins of safety for on-orbit loads of 0.2 Gsacting in any direction. (LS-71000, Section 6.3.1.3B)

3.3.9.1.1 Crew Induced Load Requirements

EUE shall provide positive margins of safety when exposed to the crew inducedloads defined in Table 3.3.9.1.1-1, Crew-Induced Loads. (LS-71000, Section6.3.1.3C)

LS-71143 - 3/3/00 3-30

TABLE 3.3.9.1.1-1. CREW-INDUCED LOADS

Crew System OrStructure

Type Of Load

Load

Direction Of Load

Levers, Handles,Operating Wheels,Controls

Push or Pullconcentrated on mostextreme edge

222.6 N (50 lbf), limit Any direction

Small Knobs Twist (torsion) 14.9 N-M (11 ft-lbf),limit

Either direction

Exposed Utility Lines(Gas, Fluid, andVacuum)

Push or Pull 222.6 N (50 lbf), limit Any direction

Cabinets and anynormally exposedequipment

Concentrated loadapplied by flat roundsurface with an area of(0.093 m2) (1 ft2)

556.4 N (125 lbf), limit Any direction

Legend:ft = feet, m = meter, N = Newton, lbf = pounds force

3.3.9.1.2 Safety Critical Structures Requirements

The VOILA EUE shall be designed in accordance with the requirements specifiedin SSP 52005. (LS-71000, Section 6.3.1.1)

3.3.9.2 Electrical Power Consuming Equipment Design

3.3.9.2.1 Batteries

All battery systems shall meet the requirements of NSTS 1700.7, ISS addendum,Section 213.2. (Derived from LS-71000, Section 6.3.2.10, NSTS 1700.7, ISSAddendum, Section 213.2)

LS-71143 - 1/28/00 4-1

4.0 VERIFICATION PROVISIONS

This section contains the minimum/mandatory requirements for qualification andacceptance test requirements and establishes guidelines for additional testingassociated with hazard and reliability screening of non-critical HRF EUE. Themethodology associated with qualification and acceptance testing will beconsistent with paragraph 4.1 of this document

A. Qualification and Acceptance Test requirements are based on Section 5.4.1 of

LS-71000.

B. Integration testing and checkout can be conducted during end item buildup.Activities such as continuity checking and interface mating will be performed.Activities such as major component operation in the installed environment,support equipment compatibility, and documentation verification will beproven during qualification.

C. Formal verification of performance characteristics occurs for the full range ofperformance requirements during qualification and for nominal operationaland critical physical requirements during acceptance. The determination ofwhether or not qualification testing is required for a particular hardware itemmust be coordinated with JSC/NT3 and HRF SE&I. Factors such as theavailability of hardware and the severity of the operational environment mustbe considered and a Combined Acceptance Plan (CAP) generated.

4.1 GENERAL

Equipment verification methods are defined as follows:

A. Inspection is a method that determines conformance to requirements by thereview of drawings, data or by visual examination of the item using standardquality control methods, without the use of special laboratory procedures.

B. Analysis is a process used in lieu of, or in addition to, other methods to ensurecompliance to specification requirements. The selected techniques mayinclude, but not be limited to, engineering analysis, statistics and qualitativeanalysis, computer and hardware simulations, and analog modeling. Analysismay also include assessing the results of lower level qualification activity.Analysis may be used when it can be determined that (1) rigorous andaccurate analysis is possible, (2) test is not cost effective, and (3) verificationby inspection is not adequate.

Verification by similarity is the process of analyzing the specification criteriafor hardware configuration and application for an article to determine if it issimilar or identical in design, manufacturing process, and quality control to anexisting article that has previously been qualified to equivalent or morestringent specification criteria. Special effort will be made to avoid

LS-71143 - 1/28/00 4-2

duplication of previous tests from this or similar programs. If the previousapplication is considered to be similar, but not equal to or greater in severity,additional qualification tests shall concentrate on the areas of new or increasedrequirements.

C. Demonstration consists of a qualitative determination of the properties of atest article. This qualitative determination is made through observation, withor without special test equipment or instrumentation, which verifiescharacteristics such as human engineering features, services, access features,and transportability. Demonstration requirements are normally implementedwithin a test plan, operations plan, or test procedure.

D. Test is a method in which technical means, such as the use of specialequipment, instrumentation, simulation techniques, and the application ofestablished principles and procedures, are used for the evaluation ofcomponents, subsystems, and systems to determine compliance withrequirements. Test shall be selected as the primary method when analyticaltechniques do not produce adequate results; failure modes exist which couldcompromise personnel safety, adversely affect flight systems or payloadoperation, or result in a loss of mission objectives; or for any componentsdirectly associated with Space Station and orbiter interfaces. The analysis ofdata derived from tests is an integral part of the test program, and should notbe confused with analysis as defined above.

4.1.1 Responsibility for Verifications

The responsibility for the performance of all verification activities is as specifiedin Appendix B. Except as otherwise specified in the contract, the provider mayuse their own or any other facility suitable for the performance of the verificationrequirements specified herein, unless disapproved by the Government. TheGovernment reserves the right to perform any of the verifications set forth in thisspecification. The Verification Compliance Matrix in Appendix B will be completed incoordination with HRF SE&I.

4.2 ACCEPTANCE AND QUALIFICATION TEST REQUIREMENTS

Sections 4.2 through 4.3 shall be used for the acceptance and qualification testingof VOILA. These sections are based on the Criticality III qualification andacceptance testing requirements in LS-71000.

LS-71143 - 1/28/00 4-3

TABLE 4.2-1. NON-CRITICAL HARDWARE QUALIFICATION TESTREQUIREMENTS

Component

TypeTest

Electronicor ElectricalEquipment

(ALL)

Functional(1)

X

ThermalCycling

7.5 Cycles(4)

X

Depress/Repress

X

RandomVibration(6) XAcousticVibration

Shock XEMC R(2)

X

X

LEGEND: R=Required; H= Hazard Screen: G= Reliability Screening

Note: Tests listed as Reliability Screening Guidelines (G) do not alleviate the responsibility to verify that thecriticality 3 equipment will meet the requirements for its intended use on the ISS.(1) Functional tests shall be conducted prior to and following each environmental test.(2) Emissions only.(3) Conducted and Radiated Susceptibility only.(4) Minimum 110 degrees F sweep required.(5) For sealed or pressurized equipment.(6) Vibration testing shall be in accordance with Section 4.2.1.2 of this document.

LS-71143 - 1/28/00 4-4

TABLE 4.2-2. NON-CRITICAL HARDWARE ACCEPTANCE TESTREQUIREMENTS

Component

TypeTest

Electronicor ElectricalEquipment

(ALL)

Functional(1)

X

ThermalCycling

1½ Cycles(3)

X

RandomVibration (4)

X

AcousticVibration

Burn-in XIntegratedFunctional

X

LEGEND: R= Required; H= Hazard Screen: G= Reliability Screening

Note: Tests listed as Reliability Screening Guidelines (G) do not alleviate the responsibility to verify that thecriticality 3 equipment will meet the requirements for its intended use on the ISS.(1.) Functional tests shall be conducted prior to and following each environmental test.(2.) 72 and Accelerated 96 hour burn in shall be performed as per Section 3.3.1.2.1 of this document.(3.) Minimum 100 degrees F sweep required.(4.) Vibration testing shall be in accordance with Section 4.2.1.2 of this document.(5.) For sealed or pressurized equipment.(6.) Performed for integrated experiment system.

4.2.1 Description of Tests

4.2.1.1 Thermal Cycle Tests

HRF payloads undergoing thermal cycle testing shall be functionally tested ateach stable temperature and during transitions. The pass-fail criteria for thefunctional test and the definition of the functional test will be equipment uniqueand shall be defined in the test plan and test procedure. Functional tests shall beconducted on end items prior to, during, and after environmental exposure.(LS-71000, Section 5.4.1.1.6)

4.2.1.1.1 Qualification Thermal Cycling

LS-71143 - 1/28/00 4-5

The Qualification Thermal Cycle Test shall be over a range of 110°F (61.1°C)centered about the normal operating temperature as defined in the individual testplans. The Qualification thermal test shall consist of 7½ cycles. One cycle isdefined as starting from normal operating temperature, increasing to themaximum high temperature, decreasing to the minimum low temperature and thenreturning to the normal operating temperature as depicted in Figure 4.2.1.1.1-1.The complete test is seven and one-half (7½) cycles with one-hour soaks at eachextreme. The hardware will be functionally tested during transitions and at thehighest and lowest temperature extremes, consistent with the defined operatingtemperature range. The hardware shall not be functionally tested at temperaturesin excess of the defined operating temperature range. (Hardware shall beunpowered when outside the manufacturer’s operating limits.) The specificprofile shall be defined in the individual test plans. (LS-71000, Section5.4.1.1.6.1)

LS-71143 - 1/28/00 4-6

A

E

F

G

H

I

A A A A A A

A A A A A A A A

B

D D D D D D D D D D D D D D D D

B C

NOTES: 1. A = Time to stabilize equipment temperature plus 1-hour minimum. 2. B = Functional tests to be performed as shown. 3. C = Control temperature range between high and low acceptance test conditions shall be a minimum of

61.11°C (110°F). Contractor is to specify tolerances on stable temperature periods. 4. D = Simplified Functional Test. Rate of temperature change during temperature transition shall not be

less than 0.55°C (1°F)/min. nor greater than 2.22°C (4°F) (4°F)/min. 5. E = Median operational temperature plus 30.56°C (55°F). 6. F = Maximum operational temperature. 7. G = Median operational temperature. 8. H = Minimum operational temperature. 9. I = Median operational temperature minus 30.56°C (55°F).

Figure 4.2.1.1.1-1. Qualification Thermal Cycling

4.2.1.1.2 Acceptance Thermal Cycling

The acceptance thermal cycle shall be conducted over a temperature range of100°F (55.6°C) centered about the hardware normal operating temperature asdefined in the test plan. The hardware shall be functionally tested before and afterthe temperature test, at each transition, and at each stable temperature. Thehardware shall not be functionally tested at temperatures in excess of the definedoperating temperature range. (Hardware shall be unpowered when outside themanufacturer’s operating limits.) One cycle is defined as starting from normaloperating temperature, increasing to the maximum high temperature, decreasingto the minimum low temperature and then returning to the normal operatingtemperature as depicted in Figure 4.2.1.1.2-1. The complete test consists of oneand one-half (1½) thermal cycles with one-hour soaks at each extreme. Minimumtemperature sweep shall be 100°F around the normal operating temperature, andthe hardware shall dwell at the temperature extremes for a minimum of 1 hour.(LS-71000, Section 5.4.1.1.6.2)

LS-71143 - 1/28/00 4-7

E

F

G

H

I

C

B/D

B

B/D

B

B/D B/D

B/D

A A

A

NOTES: 1. A = Time to stabilize equipment temperature plus 1-hour minimum. 2. B = Functional tests to be performed as shown. 3. C = Control temperature range between high and low acceptance test conditions shall be a minimum of

55.56°C (100°F). Contractor is to specify tolerances on stable temperature periods. 4. D = Simplified Functional Test. Rate of temperature change during temperature transition shall not be

less than 0.55°C (1°F)/min. nor greater than 2.22°C (4°F) (4°F)/min. 5. E = Median operational temperature plus 27.78°C (50°F). 6. F = Maximum operational temperature. 7. G = Median operational temperature. 8. H = Minimum operational temperature. 9. I = Median operational temperature minus 27.78°C (50°F).

Figure 4.2.1.1.2-1. Acceptance Thermal Cycling

4.2.1.2 Vibration Tests

Qualification for Acceptance Random Vibration Test levels are as described inSection 4.2.1.2.1. Acceptance Random Vibration Test levels are as described inSection 4.2.1.2.2

4.2.1.2.1 Qualification for Acceptance Random Vibration Test

Qualification for Acceptance Vibration Testing (QAVT) determines the numberof Acceptance Vibration Tests that may be run on flight units. QAVT shall be runon dedicated qualification test hardware only. The QAVT for HRF equipmentshall be performed at a 7.93 g rms composite level over the frequency range andspectral density defined in Table 4.2.1.2.1-1. QAVT shall be conducted at 1.69

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times the Acceptance Random Vibration Test levels. QAVT duration shall be theAcceptance Vibration Testing (AVT) duration multiplied by the number of AVTsfor which the hardware is to be qualified. (LS-71000, Section 5.4.1.1.3.2)

TABLE 4.2.1.2.1-1. QUALIFICATION ACCEPTANCE RANDOMVIBRATION TEST LEVELS

Frequency Range (Hz) Minimum Power Spectral Density (g2/Hz)

20 0.017

20 - 80 3 dB/Octave Slope

80 - 350 0.067

350 - 2000 -3 dB/Octave Slope

2000 0.0118

Composite 7.93 g rms

4.2.1.2.2 Acceptance Random Vibration Test

AVT is used to screen defects in workmanship that cannot be detected byinspection. AVT for VOILA EUE shall be performed at a 6.1 g rms compositelevel over the frequency range and minimum AVT levels defined inTable 4.2.1.2.2-1. Vibration duration shall be a minimum of 60 seconds in eachof three axes. Functional/continuity tests shall be conducted on componentsbefore, during, and after the AVT. LS-71000 Section 5.4.1.1.3.3)

LS-71143 - 1/28/00 4-9

TABLE 4.2.1.2.2-1. ACCEPTANCE RANDOM VIBRATIONWORKMANSHIP TEST LEVELS

Frequency Range (Hz) Minimum Power Spectral Density (g2/Hz)

20 0.01

20 - 80 +3 dB/Octave - Slope

80 - 350 0.04

350 - 2000 -3 dB/Octave - Slope

2000 0.007

Composite 6.1 g rms

4.2.1.3 Electromagnetic Compatibility Testing

One flight assembly shall undergo radiated emission testing and conductedemissions testing. The need to perform susceptibility tests is determined uponinitiation of the VOILA EUE project. If susceptibility tests are performed, thelevels specified in Section 3.2.7.2.1.2 shall be used. Acceptance criteria arespecified in Section 3.2.7.2.1. (LS-71000, Section 5.4.1.2.1)

4.2.1.4 Functional Testing

Abbreviated and full functional test procedures shall be as specified in a TPS or areleased procedure.

Functional tests are performed to validate the operation of the VOILA EUE flighthardware. Functionals make up the core of certain tests and can be performedbefore and after environmental testing. The functional test done prior to testingestablishes the functional state (or baseline) of the hardware while the functionaldone after testing evaluates its ability to withstand the test levels.

An abbreviated functional will be used to test the functional state of the hardwareduring some environmental testing (i.e., thermal, vibration, bench handling, etc.).The intended use of an abbreviated functional is to verify nominal hardwarefunction between test stages.

4.2.1.5 Burn-In

To the extent practical, COTS and modified COTS must meet the EEErequirements to assure the hardware/design compliance to the EEE part selectioncriteria for the proposed application and corresponding criticality. This includes arisk assessment, electrical stress analysis, and data delivery on information suchas designed/as-built EEE parts, list, construction history, Government andIndustry Data Exchange Program (GIDEP) Alerts, part obsolescence, radiationsusceptibility, and/or prior history.

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All flight assemblies utilizing non-military parts (as specified in Section 3.3.1.2)shall undergo burn-in testing. The test description can be found in Section3.3.1.2.1. (LS-71000, Section 5.4.1.1.10)

4.2.1.6 Flammability

Payload materials shall be non-flammable or self-extinguishing per the testcriteria of NASA-STD-6001, Test 1, Flammability, Odor, offgassing, andcompatibility Requirements and Test Procedures for Materials in Environmentsthat Support Combustion. The material shall be evaluated in the worst-case useenvironment at the worst-case use configuration. When the use of anonflammable material is not possible, a Material Usage Agreement (MUA) orequivalent shall be submitted to the cognizant NASA center for disposition. Iftest data does not exist for a material, the experimenter may be asked to providesamples (see NASA-STD-6001, Chapter 4) to a NASA certified test facilityMarshall Space Flight Center (MSFC) or White Sands Test Facility (WSTF) forflammability testing).

Materials transported or operated in the orbiter cabin, or operated in the ISS airlock during Extravehicular Activity (EVA) preparations, shall be tested andevaluated for flammability in the worst-case use environment of 30% oxygen and10.2 psia. Materials used in all other habitable areas shall be tested and evaluatedin the worst-case use environment of 24.1% oxygen and 15.2 psia. (LS-71000,Section 5.4.1.1.8)

4.2.1.7 Offgassing (Toxicity)

All flight hardware located in habitable areas shall be subjected to test and meetthe toxicity offgassing acceptance requirements of NASA-STD-6001, Test 7.(LS-71000, Section 5.4.1.1.9)

4.2.1.8 Bench Handling Test

A bench handling test shall be performed on the qualification unit for all stowedhardware. The bench handling test shall be conducted in accordance with MIL-STD-810, Section 516.4, I3.6, Procedure 4 or 6 with the following modifications:Test conditions of 26 drops altered to two (2) drops. Surfaces, corners, edgesshall be identified in the test procedure. (LS-71000, Section 5.4.1.1.5)

4.2.1.9 Other Tests

Depending upon the payload characteristics and how it is mounted, additionaltesting may be required. As an example, this additional testing may includeAcoustic Noise Surveys and Tests, Pressure Tests, Shock Tests, and/or SinusoidalResonance Tests as described in Section 5 of LS-71000. These tests will becoordinated with JSC/NT3 and HRF SE&I.

4.2.1.10 Pre-Delivery Acceptance Test

LS-71143 - 1/28/00 4-11

The responsible manufacturing parties shall perform a Pre-Delivery Acceptance(PDA) after the complete fabrication and assembly has been conducted for allClass I deliverable assemblies. This test shall include verification of softwareinterface and operation. The PDA must be completed before hardwarecertification testing begins. It is a full functional test and inspection that validatesthat the hardware operates per the design requirements and that it is constructedper released engineering drawings. All PDA tests shall be approved by thehardware’s JSC technical monitor and JSC/NT3, as well as the contractor qualityengineering (if applicable). The following are standard steps that each PDA testshall contain:

1. Conformance to Drawing. Verify that the hardware conforms to releasedengineering drawings.

2. No Sharp Edges. Inspect the hardware to verify that there are no sharp edgesor corners present.

3. Proper Identifying Markings. Verify that the hardware has the proper partnumber and serial number (if applicable) on it.

4. Cleanliness. All PDA tests shall include verification that all surfaces(external, internal, etc.) are to the cleanliness level of Section 3.3.1.1C of thisdocument.

4.2.1.11 Science Verification Testing

A Science Verification Testing (SVT) shall be required of the VOILA flighthardware. This is a full end-to-end functional test of the experiment system thatis conducted after environmental testing has been completed. The PrincipalInvestigator (PI) will evaluate the data resulting from the SVT for confirmationof proper function.

4.3 DOCUMENTATION OF VERIFICATION AND CERTIFICATION TESTING

The Verification Matrix (Appendix B) indicates the acceptance/qualificationcompliance plan for each applicable requirement. Once all procedures(inspection, test, analysis, or demonstration) have been completed, Appendix Bwill be filled out with the appropriate document references (e.g., TPS, waivers,reports, analysis) and used as a certification compliance matrix.

LS-71143 - 1/28/00 5-1

5.0 PREPARATION FOR SHIPMENT

{ HRF ORUs will be launched and returned in a pressurized carrier such as theMPLM, the orbiter middeck or any international transfer vehicle such as theProgress, Automated Transfer Vehicle (ATV), or other transfer vehicles. Theywill be integrated into SIR drawers, middeck/EXPRESS lockers, or ResupplyStowage Rack (RSR) trays. Large items may require soft stowageaccommodations such as the Resupply Stowage Platform (RSP) or the AisleStowage Container (ASC). Biological samples will require cold stowage in afreezer.

Analytical and physical integration of HRF ORUs will be performed by the ISSCargo Integration (CI) organization. CI has the tools and expertise necessary toperform drawer/tray/rack layout, etc. CI will also perform the actual physicalintegration of HRF stowage items in preparation for launch. Science samplesthat require late stowage may be integrated by the Utilization organization atKennedy Space Center (KSC). HRF will provide to CI all necessary data toperform these tasks such as engineering drawings of individual stowage items,weight, dimensions, hardware configuration, etc. Detailed process descriptionand data requirements will be documented in Station Program ImplementationPlan (SPIP) Volumes 3, 4, and the PIA.}

5.1 GENERAL

A. The methods of preservation, packaging, and packing used for shipment,together with necessary special control during transportation, shall adequatelyprotect the article(s) from damage or degradation in reliability or performanceas a result of the natural and induced environments encountered duringtransportation and subsequent indoor storage. (LS-71000, Section 9.1A)

B. To reduce program cost, prior to developing a newly designed container,every effort will be made by project participants to use container designsand/or containers available commercially or from Government inventories. Ifreusable containers are not available, a screening process should be initiatedfor container availability in the following priority: existing containers,commercial off-the-shelf containers, and modified commercial off-the shelfcontainers. Shipping containers and protective devices will be designed foreffective and economical manufacture, procurement, and transportability.(LS-71000, Section 9.1B)

5.2 PACKING, HANDLING, AND TRANSPORTATION

A. Packaging, handling, and transportation shall be in accordance with applicablerequirements of NHB 6000.1C, and referenced documents therein.(LS-71000, Section 9.2A)

LS-71143 - 1/28/00 5-2

B. Documented procedures and physical controls shall be established to ensurethat the HRF rack and individual items of equipment will not be subjected totemperature, shock, and humidity outside the non-operational limits duringshipment. LS-71000, Section 9.2C)

C. The VOILA EUE shall be cleaned to the “Visibly Clean Level 1 (Sensitive)”as determined in JSC-SN-C-0005, Specification Contamination ControlRequirements for the Shuttle Program. LS-71000, Section 9.2D)

5.3 PRESERVATION AND PACKING

Preservation and packing shall be in accordance with approved Packaging,Handling, and Transportation Records (PHTRs). (LS-71000, Section 9.3)

5.4 MARKING FOR SHIPMENT

Interior and exterior containers shall be marked and labeled in accordance withNHB 6000.1C including precautionary markings necessary to ensure safety ofpersonnel and facilities, and to ensure safe handling, transport, and storage.Should the individual items of equipment contain any hazardous materials,markings shall also comply with applicable requirements governing packagingand labeling of hazard materials. Packages with reuse capability shall beidentified with the words “Reusable Container - Do Not Destroy - Retain forReuse.” NASA Critical Item Labels (Form 1368 series) shall be applied inaccordance with NHB 6000.1C. (LS-71000, Section 9.4)

5.5 NASA CRITICAL SPACE ITEM LABEL

The NASA Critical Space Item Labels Form 1368 shall be affixed to exterior andinterior shipping containers in accordance with NHB 6000.1C. (LS-71000,Section 9.5A)

LS-71143 - 1/28/00 6-1

6.0 NOTES

This section contains information of a general or explanatory nature that may behelpful but is not mandatory.

6.1 DEFINITIONS

Qualification Test Test conducted as part of the verification program todemonstrate that the design and performancerequirements can be realized under specifiedconditions.

Acceptance Test Formal tests conducted to assure that the end itemmeets specified requirements. Acceptance testsinclude performance demonstrations andenvironmental exposures to screen out manufacturingdefects, workmanship errors, incipient failures, andother performance anomalies not readily detectable bynormal inspection techniques or through ambientfunctional tests.

Active Air Exchange Forced convection between two volumes. Forexample, forced convection between a subrackpayload and the internal volume of an integrated rack,or forced convection between a subrack payload andcabin air.

Continuous Noise Source A significant noise source which exists for acumulative total of eight hours or more in any 24-hourperiod is considered to be a continuous noise source.

Intermittent Noise Source A significant noise source which exists for acumulative total of less than eight hours in a 24-hourperiod is considered to be a continuous noise source.

LS-71143 - 1/28/00

APPENDIX ACRITICALITY 3 EQUIPMENT PROGRAM REQUIREMENTS

LS-71143 - 1/28/00 A-1

CRITICALITY 3 EQUIPMENT PROGRAM REQUIREMENTS

A1.0 HRF PROGRAM REQUIREMENTS

The following sections detail Criticality 3 HRF program requirements that areapplicable to all HRF Criticality 3 Projects.

A1.1 EXPERIMENT DOCUMENT

Reference: LS-20427

All EUE projects will have an Experiment Document (ED). The ED should brieflyexplain the technical need for the project and summarize how the project will meet thatneed. The overall project objective and justification should be provided. The ED willalso document agreements between the HRF Program and the EUE provider.

A1.2 DOCUMENTATION REQUIREMENTS

Documentation requirements for VOILA EUE shall be as specified in Appendix A ofthe PRD for HRF, LS-71000. Required items for submittal to NASA are summarizedbelow for convenience.

A1.2.1 Acceptance Data Package Requirements List

All flight hardware being provided under contract to NASA shall have an AcceptanceData Package (ADP) upon final delivery. The ADP will be reviewed by NASA anddiscussed at the pre-delivery acceptance review. The acceptance of any equipmentitem will be contingent upon NASA’s approval of the ADP for that item. {The tablebelow provides a typical listing of required documentation that must be included inthe ADP; not all of these requirements will be applicable for a given piece ofequipment. Actual ADP content will be as agreed upon between the HRF project andthe EUE developer. The table should be filled out to indicate which items areapplicable with any appropriate clarifying words noted in the comments column. Adescription of each product is provided after the table.}

Required forProject

# Document Yes No Comments

1 Shipping Documentation(DD250/1149)

2 Quality Log

3 Index or Table of Contents

4 Engineering Drawings

5 Inventory of Serialized Components

LS-71143 - 1/28/00 A-2

Required forProject

# Document Yes No Comments

6 Operating, Maintenance, andHandling Procedures

7 Limited Life/Time and CycleRequirements

8 “As run” Test Procedures, Data, andReports

9 Waiver requests Waiver requests are coordinatedthrough HRF SE&I

10 Safety Data

11 Structural Analyses

12 Pressure Vessel Data

13 Radioactive Material Data

14 Calibration Data

(1) Shipping Documentation: A DD250/1149 (or other Government recognized“shipper” document such as JSC Form 290), with quality control validation, willbe required for all shipments. The shipper document will indicate nomenclature,part number, serial number, and quantity of hardware shipped. The ADP shallalso be listed as an item on the shipping document. The shipping document shallidentify any end item shortages, i.e., all items missing from the shipment that arerequired to make a complete flight set and which are required by the contract.The shipper shall contain a list of all “open work” on the equipment beingshipped, i.e., all work, required by the contract, that must be done before theequipment is ready for flight.

(2) Quality Log: A chronological log of configuration and quality status of eachitem of equipment must accompany any shipment of functional hardware. A JSCForm 772, System and Component Historical Records, or equivalent, will beused for this purpose. See the Hardware Development Handbook for moreinformation.

(3) Index or Table of Contents: An index or inventory of the ADP contents. Anegative statement at the beginning of a section is required if no entry isapplicable. For example, if one of the data requirements in the table above isagreed to not be required, the section should be so noted.

(4) Engineering Drawings: As-built engineering drawings shall be provided. Thedrawings shall include the top assembly drawing for each major component andany other drawings necessary to perform receiving inspection and any test oroperation to be performed at the destination.

(5) Inventory of Serialized Components: A list of “field replaceable” serializedcomponents will be included in the ADP. The list will contain the componentpart number, component name, and component serial number.

LS-71143 - 1/28/00 A-3

(6) Operating, Maintenance, and Handling Procedures: Each delivered functionalend item shall have a separate manual covering its maintenance, repair, andoperation. The manual shall include, but not be limited to, the following (asapplicable):

a. Operational instructions suitable to support operator training and containing asystem description and general instructions for operating the equipment.

b. Any special handling, packing, transportation or storage procedures (i.e.,must be stored/transported in a specific orientation, specific environmentalconditions, etc.)

c. A list of special tools, support and facilities equipment, and all othermaterials necessary to perform maintenance.

d. A schedule chart listing the time at which all maintenance is to be performed.This shall also include inspection for required repair, maintenance, orreplacement of parts.

e. Conditions of environment in which maintenance is to be performed.

f. Detailed maintenance procedures that describe removal, disassembly, type ofmaintenance or repair, cleaning, reassemble, and reinstallation of all parts orsubassemblies. Also included shall be points of inspection and notes ofcaution.

g. Illustrated part breakdowns showing the details of the part being workedupon.

h. Schematic and interconnecting wiring diagrams in sufficient detail to enabletroubleshooting to be performed down to the replaceable subassembly orprinted circuit board level.

i. Fault analysis will be provided to facilitate maintenance. The repairprocedures shall be adequate for testing, checkout, disassembly, cleaning,inspection, repair, reassemble, adjustment, calibration, and servicing of theequipment as applicable.

(7) Limited Life/Time and Cycle Requirements: A Limited Life Items List shall beincluded which lists all items included in the shipment that have a limited lifeand what the appropriate expiration date is for each item. In addition, a list ofthe critical time/cycle items, including the total time or cycles allowed and arecord of the time or cycle used. Such time/cycle usages will be recorded on theJSC Form 772, or equivalent.

(8) “As Run” Test Procedures and Reports: The original “as run” test proceduresused for any of the testing required in this HRD, along with any associated dataand test reports shall be included in the ADP. These procedures shall includequality buy-off if applicable as documented in the Quality Plan.

(9) Waiver Requests: Any waiver requested prior to delivery against any of therequirements documented as applicable in this HRD shall be included in theADP along with any approvals granted. (Waiver requests must be coordinated

LS-71143 - 1/28/00 A-4

through HRF SE&I.)

LS-71143 - 1/28/00 A-5

(10) Safety Data: Copies of hazard reports and other safety data prepared or collectedas a result of ground and/or flight safety requirements.

(11) Structural Analyses: Copies of any structural analyses performed as specified inthis HRD or required in the contract with NASA.

(12) Pressure Vessel Data: If the hardware contains pressure vessels, this sectionshall include the appropriate documentation showing the certification, DOTrating and/or any test data.

(13) Radioactive Material Data: If the shipment contains any radioactive material,this section shall include copies of all required data on radioactive material.

(14) Calibration Data: This section shall include any calibration or scaling datarequired to interpret the output signals from or measurements made using theequipment being shipped.

LS-71143 - 1/28/00

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-1

{ If a request for deviation or waiver from the requirement stated in this SRD is anticipated or if the type of documentation supplied ormethod of verification is anticipated to not be as stated in this matrix, this information should be noted in the Comment column.}

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.1 -- Item Definition N/R -- -- -- -- Information only

3.1.1 -- Experiment Description N/R -- -- -- --

3.1.1.1 -- Experiment Overview N/R -- -- -- --

3.1.1.2 -- Operational Overview N/R -- -- -- --

3.2 -- Characteristics N/R -- -- -- --

3.2.1 -- Performance Characteristics N/R -- -- -- --

3.2.1.1C -- Functional PerformanceCharacteristics - FullExperiment Protocol Test andCheckout

9 -- Functional TPS P

3.2.1.1D -- Functional PerformanceCharacteristics - TestingDocumented on a TPS

9 -- Functional TPS P

3.2.1.1D -- Functional PerformanceCharacteristics - Demonstrateend-to-end Functionality

9 -- Functional TPS P

3.2.1.2 Equipment PerformanceCharacteristics

9 -- Functional TPS P

3.2.2 Physical Characteristics N/R -- -- -- --

3.2.2.1 Mass Properties 9 -- Test TPS I

3.2.2.2 Envelope N/R -- -- -- --

3.2.2.2.1 Stowed Envelope 9 -- Inspection Drawings I

3.2.2.2.2 Deployed Envelope N/R -- -- -- --

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-2

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.2.2.2.2.1 Hardware Protrusion Limits N/R -- -- -- --

3.2.2.2.2.1.1 6.4.4.1.1 3.12.4.1 Permanent Protrusions 9 I

3.2.2.2.2.1.2 Intermittent Protrusions N/R -- -- -- --

3.2.2.2.2.1.2A 6.4.4.1.2A 3.12.4.1 Intermittent Protrusions -Limits

9 I

3.2.2.2.2.1.2B 6.4.4.1.2B 3.12.4.1 Intermittent Protrusions -Easily Stowable

9 I

3.2.2.2.2.1.3 6.4.4.1.3 3.12.4.1 Temporary Protrusions 9 I

3.2.2.2.2.1.4 6.4.4.1.4 3.12.4.1 Clearance for CrewRestraints and Mobility Aids

9 I

3.2.2.2.2.2 Deployed EnvelopeDimensions

9 I

3.2.3 Reliability N/R -- -- -- --

3.2.3.1 Failure Propagation 9 -- Analysis FMEA I

3.2.4 Maintainability N/R -- -- -- --

3.2.4A 6.4.4.2.6.3 3.12.4.2.8.4 Unique Tools 9 ME-016 Analysis TPS I

3.2.4B 6.4.4.3.1 3.12.4.3.1 One-handed Operation 9 ME-017 Analysis orDemonstration

I

3.2.4C 6.4.4.3.2B 3.12.4.3.2A2 Connector Mate/Demate 9 ME-018 Analysis orDemonstration

I

3.2.4D 6.4.4.3.2C 3.12.4.3.2B No Damage to WiringConnectors

9 ME-018 Analysis orDemonstration

I

3.2.4E 6.4.4.2.6 3.12.4.2.8 Access to Hardware Items 9 ME-042 Analysis orDemonstration

I

3.2.4F 6.4.3.1.2A 3.12.3.1.2A Built-in Control 9 ME-008 Analysis orDemonstration

I

3.2.4G 6.4.3.1.2B 3.12.3.1.2B Access to Filters forReplacement/Cleaning

9 ME-008 Analysis orDemonstration

I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-3

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.2.4.1 Maintenance N/R -- -- -- --

3.2.4.1.1 Maintenance Functions TBD TBD Requirements to be defined.

3.2.5 Environmental Conditions N/R -- -- -- --

3.2.5.1 On-Orbit EnvironmentalConditions

N/R -- -- -- --

3.2.5.1.1 On-Orbit InternalEnvironments

N/R -- -- -- --

3.2.5.1.1.1 6.3.6.1.1 3.9.1.1 Pressure 9 Safety Hazard reports I Per NSTS 13830

3.2.5.1.1.2 6.3.6.1.2 3.9.1.2 Temperature 9 Safety Hazard reports I Per NSTS 13830

3.2.5.1.1.3 6.3.6.1.3 3.9.1.3 Humidity 9 EN-001 Analysis I

3.2.5.1.2 -- Use of Cabin Atmosphere N/R -- -- -- --

3.2.5.1.2.1 6.3.6.2.1 3.9.2.1A Active Air Exchange 9 EN-002 Inspection I

3.2.5.1.2.2 6.3.6.2.2 -- Oxygen Consumption 9 -- Analysis I

3.2.5.1.2.3 6.3.6.2.3 3.9.2.3 Chemical Releases 9 Safety Hazard reports I Per NSTS 13830

3.2.5.1.2.4 6.3.4.2 -- Cabin Air Heat Leak 9 -- I

3.2.5.1.2.5 6.3.4.3 3.5.1.13 Cabin Air Cooling 9 FD-009 Analysis I

3.2.5.1.3 -- Ionizing RadiationRequirements

N/R -- -- -- --

3.2.5.1.3.1 6.3.6.3.1 3.9.3.1 Instrument Contained orGenerated Ionizing Radiation

9 Safety Hazard reports I Per NSTS 13830

3.2.5.1.3.2 6.3.6.3.2 3.9.3.2 Ionizing Radiation Dose N/R -- -- -- --

3.2.5.1.3.3 6.3.6.3.3 3.9.3.3 Single Event Effect (SEE)Ionizing Radiation

9 EN-004 Analysis I

3.2.5.1.4 6.3.6.3.4 -- Additional EnvironmentalConditions

N/R -- -- -- --

3.2.5.1.5 -- -- Pressure Rate of Change N/R -- -- -- --

3.2.5.1.5A 6.3.1.2B 3.1.1.4B On-orbit 9 ST-003 Analysis I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-4

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.2.5.1.5B 6.3.1.2A 3.1.1.4B MPLM 9 ST-003 Analysis I

3.2.5.1.5C 6.3.1.2A -- Carrier 9 -- Analysis I

3.2.5.1.5D 6.3.1.2C 3.1.1.4K PFE 9 ST-003 Analysis I

3.2.5.2 -- -- Acoustic Emission Limits N/R -- -- -- --

3.2.5.2.1 6.4.3.3.1C 3.12.3.3.1C Continuous Emission Limits 9 EN-006 Analysis andTest

TPS I

3.2.5.2.2 6.4.3.3.2 3.12.3.3.2 Intermittent Noise Limits N/R -- -- I

3.2.5.2.2A 6.4.3.3.2A 3.12.3.3.2A A-weighted SPL Limits 9 EN-006 Analysis andTest

TPS I

3.2.5.2.2B 6.4.3.3.2 3.12.3.3.2B Cumulative Duration 9 EN-006 Analysis andTest

TPS I

3.2.5.3 6.3.4.1 3.5.1.11 Instrument SurfaceTemperature

9 FD-032 Analysis orTest

I

3.2.6 -- Transportability N/R -- -- -- --

3.2.6.1 Launch and Landing 9 I

3.2.7 Operational InterfaceRequirements

N/R -- -- -- --

3.2.7.1 Mechanical InterfaceRequirements

9 -- Test/Demonstration

TPS/Functional

I

3.2.7.1.1 3.1.1.6.1 Connector Physical Mate 9 EL-007ME-056

I

3.2.7.2 Electrical InterfaceRequirements

9 -- Test/Demonstration

TPS/Functional

I

3.2.7.2.1 -- -- Electromagnetic Radiation N/R -- -- -- --

3.2.7.2.1.1 6.3.2.4 3.2.4 ElectromagneticCompatibility (EMC)

9 EL-020 Analysis andTest

I

3.2.7.2.1.1.1 6.3.2.4.1 3.2.4.1 Electrical Grounding 9 EL-021 Analysis andTest

I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-5

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.2.7.2.1.1.2 6.3.2.4.2 3.2.4.2 Electrical Bonding 9 EL-022 Test, Analysis,and Inspection

I

3.2.7.2.1.2A 6.3.2.4.4 3.2.4.4 Meet applicable EMIrequirements of SP 30243

9 EL-020 Analysis andTest

I

3.2.7.2.1.2C 6.3.2.4.4 3.2.4.4 Alternative Use of RS03PL 9 EL-020 Analysis andTest

I

3.2.7.2.2A 6.3.2.5 3.2.4.5 ESD ≤ 4000V 9 EL-024 Analysis andInspection or

Inspection andTest

I

3.2.7.2.2B 6.3.2.5 3.2.4.5 ESD between 4000V and15000V - Labeling EPCE

9 EL-024 Analysis andInspection or

Inspection andTest

I

3.2.7.2.2C 6.3.2.5 3.2.4.5 Label of EPCE IAW MIL-STD-1686

9 EL-024 Analysis andInspection or

Inspection andTest

I

3.2.7.2.3 6.3.2.8 3.2.4.8 Corona 9 EL-024 Test orAnalysis and

Test

I

3.2.7.2.4 6.3.2.4.3 3.2.4.3 Cable/Wire Design 9 EL-021 Analysis andInspection or

Inspection andTest

I

3.2.7.2.4.1A 6.3.2.1A 3.2.3.1A Wire Derating for wirebetween EUE and UOP

9 EL-017 Analysis I

3.2.7.2.4.1B 6.3.2.1B 3.2.3.1B Wire Derating for wirebetween EUE and Rack

9 EL-017 Analysis I

3.2.7.2.4.2 6.3.2.2 3.2.3.2B Exclusive Power Feeds 9 EL-018 Analysis I

3.2.7.2.5 6.3.2.3 3.2.3.3 Loss of Power 9 Safety Hazard reports I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-6

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.2.7.2.6 6.3.2.6 3.2.4.6 AC Magnetic Fields 9 EL-020 Test I

3.2.7.2.7 6.3.2.7 3.2.4.7 DC Magnetic Fields 9 EL-020 Test I

3.2.7.3 6.3.3.2 -- Command and Data HandlingInterface Requirements

N/R -- -- -- --

3.2.7.3.1 6.3.3.1 -- Word/Byte Notations, Types,and data Transmissions

N/R -- -- -- --

3.2.7.3.1.1 6.3.3.1.1 3.3.2.1 Word/Byte Notations 9 CD-001 Inspection -- I

3.2.7.3.1.2 6.3.3.1.2 3.3.2.2 Data Types 9 CD-001 Inspection -- I

3.2.7.3.2A 6.3.3.2A -- HRF S/W Requirements -File Pathnames

9 -- I

3.2.7.3.2B 6.3.3.2B -- HRF S/W Requirements -Execution Environment

9 -- I

3.2.7.3.2C 6.3.3.2C -- HRF S/W Requirements -Consistent Results

9 -- I

3.2.7.3.2D 6.3.3.2D -- HRF S/W Requirements -DGCS and PayloadOperations Data File (PODF)P/L Display ImplementationPlan

9 -- I

3.2.7.3.2E 6.3.3.2E -- HRF S/W Requirements -Real-time data format

9 -- I

3.2.7.3.3 6.3.3.3 -- ISS C&DH Services throughHRF Common S/W Interface

9 -- I

3.2.7.4 6.3.7 -- Fire Protection InterfaceRequirements

N/R -- -- -- --

3.2.7.4.1 6.3.7.1 3.10.1 Fire Prevention 9 Safety Hazard reports I

3.2.7.4.2 6.3.7.2 -- Fire Suppression N/R -- -- -- --

3.2.7.4.2.1 6.3.7.2.1 3.10.3.1 Portable Fire Extinguisher N/R -- -- -- --

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-7

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.2.7.4.2.1A 6.3.7.2.1A 3.10.3.1A PFE Access Port 9 ME-055 Analysis andInspection

I

3.2.7.4.2.1B 6.3.7.2.1B 3.10.3.1B PFE Access Port 9 ME-055 Analysis andInspection

I

3.2.7.4.2.2 6.3.7.2.2 3.10.3.2 Fire Suppression Access PortAccessibility

9 ME-055 Demonstration I

3.2.7.4.2.3 6.3.7.2.3 3.10.3.3 Fire Suppressant Distribution 9 ME-055 Analysis orTest

I

3.2.7.4.3 6.3.7.3 3.10.4A Labeling 9 ME-055 Inspection I

3.2.7.5 Other Interface Requirements I

3.3 -- -- Design and Construction N/R -- -- -- --

3.3.1 -- -- Materials, Processes, andParts

N/R -- -- -- --

3.3.1.1 -- -- Materials and Processes N/R -- -- -- --

3.3.1.1A 6.3.8.1 3.11.1 Materials requirementsSpecified in NSTS 1700.7,ISS Addendum

9 Safety Hazard reports I Per NSTS 13830

3.3.1.1B 6.3.8.2 3.11.1.1 Commercial Parts 9 Safety Hazard reports I Per NSTS 13830

3.3.1.1C 6.3.8.3 3.11.3 Cleanliness 9 MP-002 Inspection I

3.3.1.1D 6.4.3.1.4 3.12.3.1.6 Surface Materials 9 MP-004 Inspection I

3.3.1.1E 6.3.8.4 3.11.4 Fungus Resistant Materials 9 MP-003 Inspection I

3.3.1.2 6.4.9.2 3.12.9.2 Sharp Edges 9 Safety Hazard reports I

3.3.1.2.1 6.4.9.2 -- Edge and CornerRequirements

N/R -- -- -- --

3.3.1.2.1A 6.4.9.2 -- Exposed Edge Requirementsfor Facilities and MountedHardware

N/R -- -- -- --

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-8

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.3.1.2.1A(1) 6.4.9.2 -- Exposed Edges ≥ 6.4 mmThick

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.1.2.1A(2) 6.4.9.2 -- Exposed Edges 3.0-6.4 mmThick

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.1.2.1A(3) 6.4.9.2 -- Exposed Edges 0.5-3.0 mmThick

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.1.2.1A(4) 6.4.9.2 -- Exposed Edges ≤ 0.5 mmThick

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.1.2.1B(1) 6.4.9.2 -- Exposed Corners ≤ 25mmThick

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.1.2.1B(2) 6.4.9.2 -- Exposed Corners > 25mmThick

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.1.2.1C 6.4.9.2 -- Protective Covers forPortable Equipment

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.1.2.1D 6.4.9.3 3.12.9.3 Holes 9 ME-007 Analysis andInspection

I

3.3.1.2.1E 6.4.9.4 3.12.9.4 Latches 9 ME-027 Inspection I

3.3.1.2.1F 6.4.9.5 3.12.9.5 Screws and Bolts 9 ME-026 Analysis andInspection

I

3.3.1.2.1G 6.4.9.6 3.12.9.6 Securing Pins 9 ME-053 Analysis I

3.3.1.2.1H 6.4.9.7 3.12.9.7 Levers, Cranks, Hooks, andControls

9 ME-053 Analysis andInspection

I

3.3.1.2.1I 6.4.9.8 3.12.9.8 Burrs 9 ME-053 Inspection I

3.3.1.2.1J 6.4.9.9A 3.12.9.9A Locking Wires 9 ST-009 Analysis I

3.3.1.2.1K 6.4.9.9B 3.12.9.9B Locking Wires for Fracture-Critical Fasteners

9 ST-009 Inspection I

3.3.1.2.1L 6.4.9.2 -- Locking Threaded Fasteners 9 Safety Inspection I

3.3.1.2.1M 6.4.9.2 -- Loose Equipment 9 Safety Inspection I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-9

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.3.1.3 -- -- EEE Parts Selection N/R -- -- -- --

3.3.1.3A -- -- EEE Parts Control N/R -- -- -- --

3.3.1.3B -- -- Part Selection N/R -- -- -- --

3.3.1.3C 5.4.1.1.10 -- Parts Screening 9 -- Inspection -- I

3.3.1.3.1 -- -- Burn In Screening Tests N/R -- -- -- --

3.3.1.3.1A 5.4.1.1.10 -- Burn-In Screening 9 -- Test A

3.3.1.3.1B 5.4.1.1.10 -- Full Functional Tests 9 -- Test A

3.3.2 -- Nameplates and ProductMarking

N/R -- -- -- --

3.3.2.1 6.4.7 3.12.7 Equipment Identification 9 ME-057 Inspection FPD ApprovalDocumentation

3.3.3 -- -- Workmanship 9 -- Test TPS Thermal/Vibration/Burn-In

3.3.4 -- -- Interchangeability TBD -- TBD

3.3.5 -- -- Safety N/R -- -- -- --

3.3.5.1 6.3.2.10 -- Electrical Safety 9 -- Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.5.1.1 -- -- Mating/Demating of PoweredConnectors

N/R -- -- -- --

3.3.5.1.1A 6.3.2.10.1 3.2.5.1.1 Mating/Demating of PoweredConnectors

9 Safety Analysis/Inspection

Hazard reports I Per NSTS 13830

3.3.5.1.1B 6.3.2.10.1 3.2.5.1.1 Note: Upstream Inhibit N/R -- -- -- --

3.3.5.1.2 6.3.2.10.3 3.2.5.3 Power Switches/Controls N/R -- -- -- --

3.3.5.1.2A 6.3.2.10.3A 3.2.5.3A Power Switches/ControlsOpen Supply CircuitConductors

9 EL-029 Analysis I

3.3.5.1.2B 6.3.2.10.3B 3.2.5.3B Power-offMarkings/Indications

9 EL-029 Analysis I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-10

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.3.5.1.2C 6.3.2.10.3C 3.2.5.3C Supply Circuit notCompletely Disconnected

9 EL-029 Analysis I

3.3.5.1.3 -- -- GFCI Portable EquipmentDC Sourcing voltage

N/R -- -- -- --

3.3.5.1.3A 6.3.2.10.4A 3.2.5.4A Output Voltages > 30 V rms 9 EL-030 Analysis I

3.3.5.1.3B 6.3.2.10.4B 3.2.5.4B DC Detection Independent ofSafety Wire

9 EL-030 Test I

3.3.5.1.3C 6.3.2.10.4C 3.2.5.4C AC Detection Dependent onSafety Wire

9 EL-030 Test I

3.3.5.1.3D 6.3.2.10.4D 3.2.5.4D EUE Generating InternalVoltages > 30 V rms

9 EL-030 Analysis I

3.3.5.1.3E 6.3.2.10.4E 3.2.5.4E GFCI Trip Current 9 EL-030 Test I

3.3.5.1.3F 6.3.2.10.4F 3.2.5.4F GFCI Power Removal Time 9 EL-030 Test I

3.3.5.1.3G 6.3.2.10.4G 3.2.5.4G On-Orbit Testing 9 EL-030 Analysis andDemonstration

I

3.3.5.1.3H 6.3.2.10.4 Note 3.2.5.4 Note Note: Definitions of HazardRequirements in NSTS1700.7

N/R -- -- -- --

3.3.5.1.4 6.3.2.10.5 3.2.5.5 Portable Equipment/PowerCords

N/R -- -- -- --

3.3.5.1.4A 6.3.2.10.5A 3.2.5.5A Non-battery PoweredPortable EUE

9 EL-031 Analysis I

3.3.5.1.4B 6.3.2.10.5B 3.2.5.5B Fault Currents 9 EL-031 Analysis I

3.3.6 -- -- Human Engineering N/R -- -- -- --

3.3.6.1 -- -- Intravehicular Activity (IVA)Closures and Covers DesignRequirements

N/R -- -- -- --

3.3.6.1A 6.4.3.1.1 3.12.3.1.1 Area of P/L not Designed forRoutine Cleaning

9 ME-007 Inspection I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-11

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.3.6.1B -- Note: SSP 50005, Section11.4.3 for Design Guidance

N/R -- -- -- --

3.3.6.2 6.4.3.5 -- Interior Color N/R -- -- -- --

3.3.6.2.1 -- -- Rack Mounted Equipment N/R -- -- -- --

3.3.6.2.1A 6.4.3.5.1 -- Drawer Front Panels 9 --

3.3.6.2.1B 6.4.3.5.1 -- Finish 9 --

3.3.6.2.1C 6.4.3.5.1 -- SIR Drawer Panel Latches 9 --

3.3.6.2.2 6.4.3.5.2 -- Stowed/DeployableEquipment

N/R -- -- -- --

3.3.6.2.2A 6.4.3.5.2A -- COTS Equipment - NotRepackaged

9 --

3.3.6.2.2B 6.4.3.5.2B -- Repackaged Items 9 --

3.3.6.2.3 6.4.3.5.3 -- Colors for Soft Goods 9 --

3.3.7 -- -- Anthropometry N/R -- -- -- --

3.3.7.1 -- -- Full Size RangeAccommodation

N/R -- -- -- --

3.3.7.1A 6.4.2.3 3.12.2.3 Crew Size Accommodation 9 ME-006 Analysis I

3.3.7.1B -- COTS Equipment 9 --

3.3.8 -- System Security TBD -- TBD

3.3.9 -- -- Design Requirements N/R -- -- -- --

3.3.9.1 -- -- Structural DesignRequirements

N/R -- -- -- --

3.3.9.1A 6.3.1.3A -- Positive Safety Margins forLaunch/Landing Loads

9 -- Analysis

3.3.9.1B 6.3.1.3B 3.1.1.3B Positive Safety Margins forOn-orbit Loads

9 ST-001 Analysis I

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-12

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

3.3.9.1.1 6.3.1.3C 3.1.1.3D Crew Induced LoadRequirements

9 ST-002 Analysis I

3.3.9.1.2 6.3.1.1 3.1.1.5A Safety Critical StructuresRequirements

9 ST-001-ST-004

andST-008-ST-010

Analysis andInspectionand Test

I

3.3.9.2 -- -- EPCE Design N/R -- -- -- --

3.3.9.2.1 6.3.2.10 Batteries 9 -- -- -- I

4. Verification Provisions N/R -- -- --

4.1 General N/R -- -- --

4.1.1 Responsibility forVerifications

N/R -- -- --

4.2 Verification TestRequirements

N/R -- -- --

4.2.1 Description of VerificationTests

N/R -- -- --

4.2.1.1 5.4.1.1.6 Thermal Cycling Tests 9 -- Test TPS Q/A 3 cycles, 100 degree swing

4.2.1.1.1 5.4.1.1.6.1 Qualification ThermalCycling

9 -- Test TPS Q

4.2.1.1.2 5.4.1.1.6.2 Acceptance Thermal Cycling 9 -- Test TPS A

4.2.1.2 Vibration Tests N/R -- -- -- --

4.2.1.2.1 5.4.1.1.3.2 Qualification for AcceptanceRandom Vibration Test

9 -- Test TPS Q

4.2.1.2.2 5.4.1.1.3.3 Acceptance RandomVibration Test

9 -- Test TPS A

4.2.1.3 5.4.1.2.1 Radiated and ConductedEmission Testing

9 -- Test TPS Q

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-13

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

4.2.1.4 -- Functional Testing 9 -- Test TPS Q/A/P Abbreviated and Full

4.2.1.5 5.4.1.1.10 Burn-In 9 -- Test TPS A 72 hr, 96 hr accelerated

4.2.1.6 5.4.1.1.8 Flammability 9 -- Test TPS Q/A

4.2.1.7 5.4.1.1.9 Offgassing (Toxicity) 9 -- Test TPS Q/A

4.2.1.8 5.4.1.1.5 Bench Handling Test 9 -- Test TPS Q

4.2.1.9 -- Other Tests TBD -- TBD

4.2.1.10 Pre-Delivery AcceptanceTest

9 -- Test/Demonstration/

Inspection

TPS A

4.2.1.11 Science Verification Testing 9 -- Test TPS P After all environmental testsare complete.

4.3 Documentation ofVerification and CertificationTesting

N/R -- -- -- --

5. -- Preparation for Shipment N/R -- -- -- --

5.1 -- General N/R -- -- -- --

5.1A 9.1A -- Provide Adequate Protection 9 -- A

5.1B 9.1B -- Containers N/R -- -- -- --

5.2 9.2 -- Packing, Handling, andTransportation

N/R -- -- -- --

5.2A 9.2A -- In Accordance with NHB6000.1C

9 -- A

5.2B 9.2C -- Not Subject to EnvironmentOutside of Non-OperationalLimits

9 -- A

5.2C 9.2D -- Cleanliness Requirement 9 -- A

5.3 9.3 -- Preservation and Packing 9 -- A

Q - Qualification A - Acceptance P - Performance I - IntegrationN/R - Not a requirement 9 - Requirement is applicable E - Exception N/A - Requirement is not applicable

LS-71143 - 3/3/00 B-14

APPENDIX B

VERIFICATION AND CERTIFICATION COMPLIANCE MATRIX (Cont'd)

SRDSection

LS-71000Section

SSP 57000Section Requirement Applicable

GPVPVDS # Method

VerificationDocumentation

VerificationType Responsibility Comments

5.4 9.4 -- Marking for Shipment 9 -- A

5.5 9.5 -- NASA Critical Space ItemsLabel

9 -- A

LS-71143 - 1/28/00

APPENDIX C

FUNCTIONAL REQUIREMENTS, HUMAN FACTORS, AND JHB 8080.5

LS-71143 - 1/28/00 C-1

SECTION I - FUNCTIONAL REQUIREMENTS MATRIX

X = Applicable N/A - Not Applicable E = Exception

SECTION I

FUNCTIONAL REQUIREMENTSSECTION

No. ED PARA. # Functional Requirement App. HRD Para. Comments

1

2

3

4

5

7

8

LS-71143 - 1/28/00 C-2

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

1 6.4.1.1A 3.12.1A(1) Grip Strength X ST-005

2 6.4.1.1B 3.12.1A(2) Linear Forces X ST-005

3 6.4.1.1C 3.12.1A(3) Torques X ST-005

4 6.4.1.2 3.12.1b Forces required for Maintenance X ST-005

5 6.4.2.1 3.12.2.1 Adequate Clearance X ME-021

6 6.4.2.2A 3.12.2.2A Accessibility - GeometricArrangement

X ME-021

7 6.4.2.2B 3.12.2.2B Accessibility - Access Openingsfor Fingers

X ME-021

8 6.4.2.3 3.12.2.3 Full Size RangeAccommodation

X 3.3.8.1A ME-006

9 6.4.3.1.1 3.12.3.1.1 Closures or Covers X 3.3.7.1A ME-007

10 6.4.3.1.2A 3.12.3.1.2A Built-In control - Containers X ME-008

11 6.4.3.1.2B 3.12.3.1.2B Built-In control - CaptureElements

X ME-008

12 -- 3.12.3.1.3 Deleted from SSP 57000 N/A --

13 -- 3.12.3.1.4 Deleted from SSP 57000 N/A --

14 6.4.3.1.3 3.12.3.1.5 One-handed Operation X ME-009

15 6.4.3.1.4 3.12.3.1.6 Surface Materials X 3.3.1.1C MP-004

16 6.4.3.2.1 3.12.3.2.1 Continuous/Incidental Contact -High Temperature

X Safety

17 6.4.3.2.2 3.12.3.2.2 Continuous/Incidental Contact -Low Temperature

X Safety

LS-71143 - 1/28/00 C-3

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

18 6.4.3.3 3.12.3.3 Acoustic Design Requirementsfor Payloads

NR --

19 6.4.3.3.1C 3.12.3.3.1 Continuous Noise Limits -Independently OperatedEquipment

X 3.2.5.4 EN-006

20 6.4.3.3.2 3.12.3.3.2 Intermittent Noise Limits X EN-006

21 6.4.3.4A 3.12.3.4a Work Surface Reflection andSpecularity

X ME-043

22 6.4.3.4B 3.12.3.4b Lighting Levels X ME-043

23 6.4.3.4C 3.12.3.4c Dimmable Light Sources X ME-043

24 6.4.3.4D 3.12.3.4d Glovebox Lighting X ME-043

25 6.4.3.4E 3.12.3.4e Use of ISS Portable Utility Light X ME-043

26 6.4.3.5.1 -- Color Scheme - Rack MountedEquipment

N/A -- Equipment is stowed, not rackmounted.

27 6.4.3.5.2A -- Color Scheme -Stowed/Deployable Equipment -COTS, not repackaged

X --

28 6.4.3.5.2B -- Color Scheme -Stowed/Deployable Equipment,repackaged items

X --

29 6.3.5.3 -- Colors for Soft Goods X --

30 6.4.4.1.1 3.12.4.1 Permanent Protrusions X 3.2.2.2.2.1.1 --

31 6.4.4.1.2A 3.12.4.1 Intermittent Protrusions X 3.2.2.2.2.1.2A --

32 6.4.4.1.2B 3.12.4.1 Intermittent Protrusions - EasilyStowable

X 3.2.2.2.2.1.2B --

LS-71143 - 1/28/00 C-4

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

33 6.4.4.1.3 3.12.4.1 Temporary Protrusions X 3.2.2.2.2.1.3 --

34 6.4.4.1.5 3.10.3.2 Fire Suppression Port Access X ME-055

35 6.4.4.2.1 3.12.4.2.1 Equipment Mounting X ME-011

36 6.4.4.2.2A 3.12.4.2.2 Drawers and Hinged Panels - forroutine checkout of P/L ORUs

X ME-012

37 6.4.4.2.2B 3.12.4.2.2 Drawers and Hinged Panels -remain open without manualsupport

X ME-012

38 -- 3.12.4.2.3 Deleted from SSP 57000 N/A --

39 -- 3.12.4.2.4 Deleted from SSP 57000 N/A --

40 6.4.4.2.3 3.12.4.2.5 Alignment X ME-013

41 -- 3.12.4.2.5.1 Deleted from SSP 57000 N/A --

42 6.4.4.2.4 3.12.4.2.6 Slide-Out Stops X ME-002

43 6.4.4.2.5 3.12.4.2.7 Push-Pull Force X ST-006

44 6.4.4.2.6 3.12.4.2.8 Access X ME-042

45 6.4.4.2.6.1A 3.12.4.2.8.1 Covers - sliding or hinged cap ordoor

X ME-007

46 6.4.4.2.6.1B 3.12.4.2.8.1 Covers - quick-opening coverplate

X ME-007

47 6.4.4.2.6.2 3.12.4.2.8.2 Self-Supporting Covers X ME-007

48 -- 3.12.4.2.8.3 Deleted from SSP 57000 N/A --

49 6.4.4.2.6.3 3.12.4.2.8.4 Unique Tools X 3.2.4A ME-016

50 6.4.4.3.1 3.12.4.3.1 One-Handed Operation X ME-017

LS-71143 - 1/28/00 C-5

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

51 6.4.4.3.2A 3.12.4.3.2a(1) Accessibility - mate/demate -Nominal Operations

X ME-018

52 6.4.4.3.2B 3.12.4.3.2a(2) Accessibility - mate/demate -Maintenance Operations

X ME-018

53 6.4.4.3.2C 3.12.4.3.2b Accessibility - no damage towiring connectors

X ME-018

54 6.4.4.3.3 3.12.4.3.3 Ease of disconnect X ME-017

55 6.4.4.3.4 3.12.4.3.4 Indication of Pressure Flow X ME-050

56 6.4.4.3.5 3.12.4.3.5 Self Locking X ME-017

57 6.4.4.3.6A 3.12.4.3.6A Connector Arrangement - Spacebetween Connectors andAdjacent Obstructions

X ME-018

58 6.4.4.3.6B 3.12.4.3.6B Connector Arrangement - Spacebetween Connectors in a Row

X ME-018

59 6.4.4.3.7 3.12.4.3.7 Arc Containment X EL-026

60 6.4.4.3.8 3.12.4.3.8 Connector Protection X ME-019

61 6.4.4.3.9 3.12.4.3.9 Connector Shape X 3.3.10.4.1A ME-019

62 6.4.4.3.10 3.12.4.3.10 Fluid and Gas Line Connectors X 3.3.10.4.1B FD-001

63 6.4.4.3.11 3.12.4.3.11A Alignment Marks or Guide Pins X ME-020

64 -- 3.12.4.3.11B Deleted from SSP 57000 N/A --

65 6.4.4.3.12A 3.12.4.3.12A Coding - Unique to Connection X ME-020

66 6.4.4.3.12B 3.12.4.3.12B Coding - Visible X ME-020

67 6.4.4.3.13 3.12.4.3.13 Pin Identification X EL-007

68 6.4.4.3.14 3.12.4.3.14 Orientation X ME-020

LS-71143 - 1/28/00 C-6

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

69 6.4.4.3.15A 3.12.4.3.15a Hose/Cable Restraints - LooseEnds

X ME-022

70 6.4.4.3.15B 3.12.4.3.15b Hose/Cable Restraints - Clamps X ME-022

71 6.4.4.3.15C 3.12.4.3.15c Hose/Cable Restraints - MultipleCables

NR --

72 6.4.4.3.15D 3.12.4.3.15d Hose/Cable Restraints - Lengths X ME-022

73 6.4.4.4.1 3.12.4.4.1 Non-Threaded Fasteners StatusIndication

X ME-023

74 6.4.4.4.2 3.12.4.4.2 Mounting Bolt/Fastener Spacing X ME-024

75 -- 3.12.4.4.3 Deleted from SSP 57000 N/A --

76 6.4.4.4.3 3.12.4.4.4A Multiple Fasteners - IdenticalType

X ME-025

77 -- 3.12.4.4.4B Deleted from SSP 57000 N/A --

78 6.4.4.4.4 3.12.4.4.5 Captive Fasteners X ME-026

79 6.4.4.4.5A 3.12.4.4.6A Quick Release Fasteners - Oneturn max

X ME-026

80 6.4.4.4.5B 3.12.4.4.6B Quick Release Fasteners -Positive Locking

X ME-026

81 6.4.4.4.6 3.12.4.4.7 Threaded Fasteners X ME-026

82 6.4.4.4.7A 3.12.4.4.8A Over Center Latches - Nonself-latching

X ME-027

83 6.4.4.4.7B 3.12.4.4.8B Over Center Latches - LatchLock

X ME-027

84 6.4.4.4.7C 3.12.4.4.8C Over Center Latches - LatchHandles

X ME-027

LS-71143 - 1/28/00 C-7

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

85 6.4.4.4.8 3.12.4.4.9 Winghead Fasteners X ME-026

86 -- 3.12.4.4.10 Deleted from SSP 57000 N/A --

87 6.4.4.4.9A 3.12.4.4.11A Fastener Head Type - On-OrbitCrew Actuation

X ME-028

88 6.4.4.4.9B 3.12.4.4.11B Fastener Head Type - SmoothSurface

X ME-028

89 6.4.4.4.9C 3.12.4.4.11C Fastener Head Type - SlottedFasteners

X ME-028

90 6.4.4.4.10 3.12.4.4.12 One-Handed Actuation X ME-029

91 6.4.4.4.11 3.12.4.4.13 Accessibility X ME-024

92 6.4.4.4.12 3.12.4.4.14 Access Holes X ME-024

93 6.4.5.1 3.12.5.1 Controls Spacing DesignRequirements

X ME-030

94 6.4.5.2.1 3.12.5.2.1 Protective Methods NR --

95 6.4.5.2.1A 3.12.5.2.1a Protective Methods -Location/Orientation

X ME-031

96 6.4.5.2.1B 3.12.5.2.1b Protective Methods -Recess/Shielding

X ME-031

97 6.4.5.2.1C 3.12.5.2.1c Protective Methods -Cover/Guard, No Safety or LockWire

X ME-031

98 6.4.5.2.1D 3.12.5.2.1d Protective Methods -Obscuration by Cover Guards

X ME-031

99 6.4.5.2.1E 3.12.5.2.1e Protective Methods - Interlocks X ME-031

100 6.4.5.2.1F 3.12.5.2.1f Protective Methods - Resistance X ME-031

LS-71143 - 1/28/00 C-8

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

101 6.4.5.2.1G 3.12.5.2.1g Protective Methods - PositionLocks for Sequencing

X ME-031

102 6.4.5.2.2 3.12.5.2.2 Noninterference X ME-030

103 6.4.5.2.3 3.12.5.2.3 Dead-Man Controls X Safety

104 6.4.5.2.4 3.12.5.2.4 Barrier Guards X ME-030

105 6.4.5.2.5 3.12.5.2.5 Recessed Switch Protection X ME-031

106 -- 3.12.5.2.6 Deleted from SSP 57000 N/A --

107 6.4.5.2.7 3.12.5.2.7 Position Indication X ME-032

108 6.4.5.2.8 3.12.5.2.8 Hidden Controls X ME-031

109 6.4.5.2.9 3.12.5.3.9 Hand Controllers X ME-031

110 6.4.5.3A 3.12.5.3a Valve Controls - Low-TorqueValves

X ME-033

111 6.4.5.3B 3.12.5.3b Valve Controls - Intermediate-Torque Valves

X ME-033

112 6.4.5.3C 3.12.5.3c Valve Controls - High-TorqueValves

X ME-033

113 6.4.5.3D 3.12.5.3d Valve Controls - HandleDimensions

X ME-033

114 6.4.5.3E 3.12.5.3e Valve Controls - Rotary ValveControls

X ME-033

115 6.4.5.4 3.12.5.4 Toggle Switches X ME-034

116 6.4.6 3.12.6 Restraints and Mobility Aids X ME-035

117 6.4.6.1A 3.12.6.1A Stowage Drawer ContentsRestraints - Items do not Float

X ME-036

LS-71143 - 1/28/00 C-9

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

118 6.4.6.1B 3.12.6.1B Stowage Drawer ContentsRestraints - Items do not JamDrawer

X ME-036

119 6.4.6.1C 3.12.6.1C Stowage Drawer ContentsRestraints - ItemsRemoval/Replacement

X ME-036

120 6.4.6.2A 3.12.6.2A Stowage and EquipmentDrawers/Trays - Open/CloseWith One Hand

X ME-027

121 6.4.6.2B 3.12.6.2B Stowage and EquipmentDrawers/Trays - Latch Design

X ME-027

122 6.4.6.3 3.12.6.3 Captive Parts X ME-036

123 6.4.6.4.1 3.12.6.4.1 Handles and Restraints X ME-037

124 -- 3.12.6.4.2 Deleted from SSP 57000 N/A --

125 6.4.6.4.2 3.12.6.4.3 Handle Location/Front Access X ME-037

126 6.4.6.4.3 3.12.6.4.4 Handle Dimensions X ME-037

127 6.4.6.4.4A 3.12.6.4.5A Non-Fixed Handles DesignRequirements - Stop Position

X ME-037

128 6.4.6.4.4B 3.12.6.4.5B Non-Fixed Handles DesignRequirements - One Hand Use

X ME-037

129 6.4.6.4.4C 3.12.6.4.5C Non-Fixed Handles DesignRequirements -Locked/Unlocked Indication

X ME-037

130 6.4.7 3.12.7 Identification Labeling X ME-057

131 6.4.8 3.12.8 Color - Interior Colors X ME-047

LS-71143 - 1/28/00 C-10

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

132 6.4.9.1A 3.12.9.1A Electrical Hazards - Exposurehazard below threshold forshock

NR --

133 6.4.9.1B 3.12.9.1B Electrical Hazards - Exposurehazard exceeds threshold forshock

X EL-041

134 6.4.9.1C 3.12.9.1C Electrical Hazards - Exposurehazard exceeds threshold forshock and threshold of let-goprofile

X EL-041

135 6.4.9.1D 3.12.9.1D Electrical Hazards -Twodependent controls provided

X EL-041

136 6.4.9.1E 3.12.9.1E Electrical Hazards -Threeindependent hazard controls

X EL-041

137 6.4.9.1.1A 3.12.9.1.1 Mismatched - ReversedConnection

X ME-019

138 6.4.9.1.1B 3.12.9.1.1 Mismatched - BlindConnections

X ME-019

139 6.4.9.1.1C 3.12.9.1.1 Mismatched - Mismating X ME-019

140 6.4.9.1.1D 3.12.9.1.1 Mismatched -MinimizingEquipment Risk

X ME-019

141 -- 3.12.9.1.2 Deleted from SSP 57000 N/A --

142 -- 3.12.9.1.3 Deleted from SSP 57000 N/A --

143 6.4.9.1.2.1 3.12.9.1.4.1 Device Accessibility X EL-013

144 6.4.9.1.2.2 3.12.9.1.4.2 Extractor-Type Fuse Holder X EL-013

145 6.4.9.1.2.3 3.12.9.1.4.3 Overload Protection Location X EL-013

LS-71143 - 1/28/00 C-11

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

146 6.4.9.1.2.4 3.12.9.1.4.4 Overload ProtectionIdentification

X EL-013

147 6.4.9.1.2.5 3.12.9.1.4.5 Automatic Restart Protection X EL-013

148 -- 3.12.9.1.5 Deleted from SSP 57000 N/A --

149 -- 3.12.9.1.5.1 Deleted from SSP 57000 N/A --

150 6.4.9.2 3.12.9.2 Sharp Edges and CornersProtection

X 3.3.1.1.1 Safety

151 6.4.9.3 3.12.9.3 Holes X 3.3.1.1.1.1D ME-007

152 6.4.9.4 3.12.9.4 Latches X 3.3.1.1.1.1E ME-027

153 6.4.9.5 3.12.9.5 Screws and Bolts X 3.3.1.1.1.1F ME-026

154 6.4.9.6 3.12.9.6 Securing Pins X 3.3.1.1.1.1G ME-053

155 6.4.9.7 3.12.9.7 Levers, Cranks, Hooks, andControls

X 3.3.1.1.1.1H ME-053

156 6.4.9.8 3.12.9.8 Burrs X 3.3.1.1.1.1I ME-053

157 6.4.9.9A 3.12.9.9A Locking Wires - FastenersWhich Must be Unfastened On-Orbit

X 3.3.1.1.1.1J ST-009

158 6.4.9.9B 3.12.9.9B Locking Wires - FractureCritical Fasteners

X 3.3.1.1.1.1K ST-009

159 6.4.9.10A 3.12.9.10A Audio Displays - False Alarms X ME-044

160 -- 3.12.9.10B Deleted from SSP 57000 N/A --

161 6.4.9.10C 3.12.9.10C Audio Displays - OperabilityTesting

X ME-044

162 6.4.9.10D 3.12.9.10D Audio Displays - ManualDisable

X ME-044

LS-71143 - 1/28/00 C-12

SECTION II - HUMAN FACTORS REQUIREMENTS MATRIX (Cont'd)

X - Applicable N/A - Not Applicable E - Exception NR - Not a Verifiable Requirement

SECTION II

HUMAN FACTORSREQUIREMENTS SECTION

No. LS-71000 Section SSP 57000 Section Human Factors Requirement App. HRD Section. GPVP VDS # Comments

163 -- 3.12.9.11 Deleted from SSP 57000 N/A --

164 6.4.9.11 3.12.9.12 Egress X Safety

165 6.4.10 3.12.10 Payload In-Flight Maintenance X 3.4.1 ME-003

166 -- 3.12.11 Deleted from SSP 57000 N/A --

LS-71143 - 1/28/00 C-13

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

G-1 Equipment Accessibility forMaintenance

X Inspect drawing, design, and hardware

G-2 Separation of Redundant Equipment X Ref. Hardware Item FMEA/Critical Items List (CIL)

G-3 Systems Checkout Provisions X Inspect drawing, design, and hardware

G-4 Protection of Spacecraft Electrical andMechanical Systems from Debris

X Inspect drawing and design

G-5 Interior Design of Spacecraft forCleanliness

X

G-6 Redundancy Requirements X

G-7 Time Displays X

G-8 Redundant Paths - Verification ofOperation

X

G-9 Shatterable Material - Exclusion FromHabitable Compartment

X Inspect H/W Item drawing and design

G-10 Control of Limited- Life Components X

G-11 Procurement Document Identificationfor Manned Space Flight Vehicle Items

X Audit procurement documents as necessary

G-12 Application of Previous QualificationTests

X

G-13 Shipping and Handling Protection forSpace Flight Hardware

X

G-14 Identification and Classification ofFlight and Non-flight Equipment

X

G-15 Equipment Failure - Verification ofFlight Readiness

X Discrepancy Report (DR) and Failure InvestigationAnalysis Report (FIAR) Systems in place

LS-71143 - 1/28/00 C-14

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

G-16 Operating Limits on Temperature -Controlled Equipment

X

G-17 Separate Stock for Space Flight Partsand Materials

X Reference assembly TPSs and ADP for evidence oftraceability

G-18 Safety Precautions - Test and OperatingProcedures

X Audit Test Procedures

G-19 Special Processes - Identification ofDrawings

X Review Drawings. Applicable to Class I flightequipment only.

G-20 Spacecraft Equipment - Protection fromSystem Liquids

X

G-21 Spacecraft Equipment - MoistureProtection

X Applicable to pressurized compartment

G-22 Parts Identification X Reference assembly TPSs and ADP for evidence oftraceability

G-23 Pressure Garment Wiring - Ignition ofMaterials by Electrical Current

X

G-24 GSE and Airborne Support EquipmentProtective Devices

X

G-25 Thermal Design and Analysis - ThermalParameters

X

G-26 Internally Generated Radiation X

G-27 Fire Control X

G-28 Sealing - Solid Propellant RocketMotors

X

G-29 Reentry Propulsion Subsystem In-FlightTest

X

LS-71143 - 1/28/00 C-15

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

G-30 Switch Protection Devices X

G-31 Detachable Crew-Operated Tools -Restriction in Spacecraft

X

G-32 Measurement Systems That DisplayFlight Information to the Crew -Indication of Failure

X

G-33 Surface Temperatures X

G-34 Extravehicular Activity ElectronicConnectors

X

G-35 Enclosure Panels External to theHabitable Modules

X

G-36 Thermal Blankets - ExtravehicularActivity

X

G-37 Verification of Adequate ExternalVisibility

X

G-38 Pressurization or Repressurization -Precluding Ingress of UndesirableElements

X

G-39 Lightning Protection Design X

G-40 Radioactive Luminescent Devices X

G-41 Acoustic Noise Criteria X

G-42 Solar Wind Environment X

G-43 Centralized Subsystem Controls X

G-44 Attitude Control Authority X

G-45 Solid Propellant Rocket Motors -Ignition Capability with UnsealedNozzle

X

LS-71143 - 1/28/00 C-16

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

G-46 Separation Sensing System - StructuralDeformation

X

G-47 Gyroscopes - Verification of RotationalSpeed or Drift Rate

X

G-48 Onboard Experiments - Required Pre-installation Checklist

X

G-49 Temperature and Pressure MonitoringRequirements of Hydrogen PeroxideSystems

X

G-50 Direct Procurement of Parts X Audit Procurement Documentation

G-51 Flight Hardware - Restriction on Use forTraining

X Controlled through TPSs

G-52 Reuse of Flight Hardware X

ELECTRICAL

E-1 Mating Provisions for ElectricalConnectors

X

E-2 Protection of Severed Electrical Circuits X

E-3 Electrical and Electronic Devices -Protection from Reverse Polarity and/orOther Improper Electrical Inputs

X

E-4 Electrical Connectors - MoistureProtection

X

E-5 Electrical Connectors - Pin Assignment X

E-6 Corona Suppression X

E-7 Tantalum Wet Slug Capacitors -Restriction on Use

X Review Hardware drawings and design

LS-71143 - 1/28/00 C-17

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

E-8 Electrical and Electronic Supplies andLoads - Verification Tests

X Review TPSs

E-9 Electrical Circuits - De-energizingRequirements

X Review Drawings, Design, and Test Procedures

E-10 Cleaning of Electrical and ElectronicEquipment

X

E-11 Protective Covers or Caps for ElectricalReceptacles and Plugs

X

E-12 Electrical Connectors - Disconnectionfor Troubleshooting and Bench Testing

X

E-13 Bioinstrumentation Systems - CrewElectrical Shock Protection

X Review Drawings and Design, Test protectioncircuits as part of PDA.

E-14 Electrical Wire Harness - DielectricTests

X Ref. Assembly TPS

E-15 Electrical Power Distribution Circuits -Overload Protection

X Review hardware item design and drawings

E-16 Testing Protective Devices for Solid-State Circuits

X

E-17 Electrical and Electronic Piece Parts -Closure Construction

X

E-18 Circuitry for Automatic Shutdown ofLaunch Vehicle Engine(s)

X

E-19 Equipment Design - Power Transients X

E-20 Control of Electrostatic Discharge forElectronic Parts and Assemblies

X

E-21 Electrical Connectors X

E-22 Ionizing Radiation Effects X

LS-71143 - 1/28/00 C-18

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

E-23 Transistors - Selection of Types X

E-24 Electrical Wire and Cable AcceptanceTests

X

FLUIDS

F-1 Flow Restriction Requirements -Pressurized Sources

X

F-2 Moisture Separators in a Zero-GravityEnvironment

X

F-3 Service Points - Positive ProtectionFrom Interchangeability of FluidService Lines

X

F-4 Ground Service Points - Fluid Systems X

F-5 Fluid Lines - Separation Provisions X Applicable only to planned vehicle separation

F-6 Temperature and Pressure MonitoringRequirements for Potentially HazardousReactive Fluids

X

F-7 Capping of Servicing and Test Ports X

F-8 Fluid System Components WhoseFunction is Dependent on Direction ofFlow - Protection Against IncorrectInstallation

X

F-9 Spacecraft Venting - Induced PerturbingForces

X

F-10 Nozzles and Vents - Protection Prior toLaunch

X

F-11 Fluid Supplies - Verification Tests X

LS-71143 - 1/28/00 C-19

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

F-12 Protection of Pressurized Systems fromDamage Due to Pressurant Depletion -GSE and Airborne Support Equipment

X

F-13 Crew Cabin Module Pressure - VentingRestriction

X

F-14 Crew Cabin Module Ventilating Fans -Protection from Debris

X

F-15 Separation of Hypergolic Reactants X

F-16 Fluid Line Installation X

F-17 Cleanliness of Flowing Fluids andAssociated Systems

X

F-18 Pressure Relief Valves - Standardizationof Functional Testing

X

F-19 Protection for Tubing, Fittings, andFluid System Components - FlightHardware and Associated Equipment

X

F-20 Fluid Systems - Cleanliness X

F-21 Purge Gases - Temperature andHumidity Requirements

X

F-22 Pressure Garments - Protection AgainstFailure Propagation

X

F-23 Qualification Fluid X

F-24 Fluid Systems - Design for Flushing andDraining

X

F-25 Toxicity - Fluids Contained in Systemsin the Crew Compartment

X

LS-71143 - 1/28/00 C-20

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

F-26 Atmospheric Pressure and CompositionControl

X

F-27 Liquid or Gas Containers - Verificationof Contents

X

F-28 Use of Halogen Method for CoolantSystem Leak Detection

X

F-29 Filter Protection of Active FluidComponents

X Review Hardware Item design and drawings

F-30 Pressure Relief for Pressure Vessels X

MATERIALS ANDPROCESSES

M/P-1 Material Selection, Review, andDrawing Sign-off

X Review Hardware Item Material Review Cert.

M/P-2 Flammability of Wiring Material X Review Hardware Item Material Review Cert.

M/P-3 Toxicity of Materials Used in CrewCompartments - Wire Insulation, Ties,Identification Marks, and ProtectiveCoverings

X Review Hardware Item Material Review Cert.

M/P-4 Metals and Metal Couples - Restrictionon Use

X Review Hardware Item Material Review Cert.

M/P-5 Solutions Which Contain EthyleneGlycol - Requirements for SilverChelating Agent

X

M/P-6 Toxicity - Requirements forNonmetallic Materials Proposed for UseWithin Crew Compartment

X Review Hardware Item Material Review Cert.

LS-71143 - 1/28/00 C-21

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

M/P-7 Material Detrimental to ElectricalConnectors

X Review Hardware Item Material Review Cert.

M/P-8 Leak Detectors - Wetting Agents X

M/P-9 Breathing Systems - Requirement toTest for Mercury Contamination

X

M/P-10 Liquid Locking Compounds,Restrictions, and Controls

X

M/P-11 Pressure Vessel Documentation X

M/P-12 Multi-Layer Blanket Bake-Out X

M/P-13 Pressure Vessel Design X

M/P-14 Silicate Ester Coolant System Design X

M/P-15 Mercury - Restriction on Use X

M/P-16 Restriction on Coatings for AreasSubject to Abrasion

X

M/P-17 Radiographic Inspection of Brazed andWelded Tubing Joints

X

M/P-18 Etching Fluorocarbon InsulatedElectrical Wire

X

M/P-19 Spacecraft Material - Restriction on Useof Polyvinyl Chloride

X

M/P-20 Titanium or its Alloys - Prohibited UseWith Oxygen

X

M/P-21 Beryllium - Restricted Use Within CrewComponents

X

M/P-22 Brazed Joints - Identification Marks X

LS-71143 - 1/28/00 C-22

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

M/P-23 Pressure Vessels - MaterialsCompatibility and Vessel QualificationsTests

X

M/P-24 Cadmium - Restriction on Use X

M/P-25 Pressure Vessels - NondestructiveEvaluation Plan

X

M/P-26 Repair of Sandwich - Type Structures X

MECHANICAL ANDSTRUCTURAL

M/S-1 Equipment Containers - Design ForRapid Spacecraft Decompression

X Review drawings and design, Test if necessary

M/S-2 Alignment of Mechanical Systems X

M/S-3 Wire Bundles - Protective Coating X

M/S-4 Hatches - Repeated Use X

M/S-5 Threaded Fittings - Restrictions onRelease of Particles and ForeignMaterials

X

M/S-6 Exposed Sharp Surfaces or Protrusions X

M/S-7 Windows and Glass Structure X

M/S-8 Penetration of Inhabited SpacecraftCompartments

X

M/S-9 Mechanisms X

M/S-10 Functional Doors That Operate in Flight X

M/S-11 Meteoroid Protection Levels forStructures

X

M/S-12 Spacecraft Recovery Hoist Loops X

LS-71143 - 1/28/00 C-23

SECTION III - JHB 8080.5 DESIGN GUIDANCE MATRIX (Cont'd)

X = Applicable N/A - Not Applicable E = Exception

SECTION III

JHB 8080.5 DESIGN GUIDANCESECTION

No. Standard # Abbreviated Requirement App. HRD Section Comments

M/S-13 Lifting and Hoisting GSE Identification X

M/S-14 Structural Analysis X

M/S-15 Stainless Steel Tubing - Method ofJoining

X

M/S-16 Pressure Vessels - Negative PressureDamage

X

PYROTECHNIC

P-1 Explosive Devices - Arming andDisarming

X

P-2 Pyrotechnic Devices - PreflightVerification Tests at Launch Sites

X

P-3 Wire Splicing X

P-4 Explosive Devices - Packaging Material X

P-5 Explosive Devices - IdentificationRequirements

X

P-6 Protection of Electrical Circuitry forExplosive Devices Employing HotBridge Wire Initiators

X

P-7 Explosive Devices - Color CodingRequirements

X