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SSP 53074-PVP, Draft 1

Export Administration Regulations (EAR) Notice

This document contains information controlled by the Export Administration Regulations (EAR), 15 CFR 730-774, and has been classified as EAR99.

SSP 53074-PVP, Draft 16/28/02

(This Page Intentionally Blank)

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FOREWORD

INTERNATIONAL SPACE STATION PROGRAM

EXPRESS RACK PAYLOAD VERIFICATION PLAN FOR PGBA-5

This document provides the complete set of verification requirements necessary to verify compliance with interface compatibility and safety design-to requirements for the PGBA-5 payload.

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DOC. NO.: SSP 53074-PVP, Draft 1

DOCUMENT RELEASE RECORD (DRR)Update this document by:

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i thru x1-1 thru 1-6A-i thru A-iiA-1 thru A-2B-i thru B-iiB-1 thru B-164C-i thru C-iiC-1 thru C-6

DPD 681, Section 3, DR SE47. Document Draft 1 being provided to MSFC for baselining per DR SE47 and NAS8-50000 CoTR e-mail direction dated 11/14/01, 10:58 a.m.

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TABLE OF CONTENTS

SECTION PAGE

TITLE PAGE........................................................................................ iSIGNATURE PAGE............................................................................ iiiFOREWORD........................................................................................ vDOCUMENT RELEASE RECORD.................................................... viiTABLE OF CONTENTS...................................................................... ix

1. INTRODUCTION............................................................................... 1-11.1 PURPOSE............................................................................................. 1-11.2 THE VERIFICATION REQUIREMENT DEFINITION SHEET....... 1-11.2.1 VRDS Header........................................................................................ 1-11.2.2 VRDS Body............................................................................................ 1-41.3 EXCEPTIONS/EXCEPTION PROCESSING..................................... 1-5

APPENDIXES:

A VERIFICATION DEVIATION TABLE.............................................. A-iB VERIFICATION REQUIREMENT DEFINITION SHEETS............. B-iC ABBREVIATIONS AND ACRONYMS............................................. C-i

LIST OF FIGURES

FIGURE PAGE

1-1 VRDS FORM........................................................................................ 1-2

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SECTION 1, INTRODUCTION

1.1 PURPOSE

The Payload Verification Plan (PVP) encompasses the complete set of verification requirements that address safety and interface compatibility of the PGBA-5. The PVP requirements pertain to all phases of operations, including ascent/descent, on-orbit integration, and on-orbit operations.

This plan is developed in accordance with the payload verification process described in SSP 52000-PVP-ERP and SSP 52000-PVP-ERP/IA.

1.2 THE VERIFICATION REQUIREMENT DEFINITION SHEET

The VRDS form (Figure 1-1) is separated into two parts, the header and the body.

1.2.1 VRDS Header

The header is used for identification and tracking purposes and contains:

A. Verification Number

(1) (2) (3)AA - AA – NNN

(1) Discipline Identifier [2 digits (alpha)]

ST - StructuralME - MechanicalEL - ElectricalEM - Electromagnetic Interference/Electromagnetic

Compatibility (EMI/EMC)CD - Command and Data HandlingTH - Thermal ControlVC - VacuumGA - GasesEN - EnvironmentalFP - Fire ProtectionMP - Materials and PartsHF - Human FactorsSA - Safety

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VERIFICATION REQUIREMENT DEFINITION SHEET

Verification Number Requirement Title Verification Method

AA-AA-NNN Example VRDS A/T/I/D

Hazard Report Number

Verification Requirement:

The IDD requirement paragraph number and a restatement of the IDD/ICD requirement that must be verified to ensure payload hardware/software interface compatibility and safety (Paragraph Number).

Description of Verification Method:Instructions and details suggesting how the verification method(s), as identified in the header, should be implemented (what analyses, tests, inspections, or demonstrations are required and implementation details). In addition, any related clarification deemed necessary to further explain what is required will be provided.

Required Verification Data:

Certificate of Compliance with (COC) the requirement.

OR

Integrated Rack Analysis Data.

Data Submittal Dates:

L-TBD mo

L-TBD mo

Description of Reverification Requirements:

Normally the same as “Verification Method,” but if different will be detailed here.

Required Reverification Data:

Certificate of Compliance (COC) with the requirement.

OR

Integrated Rack Analysis Data.

Data Submittal Dates:L-TBD moL-TBD mo

Applicable Documents and Notes:

SSP-52000-IDD-ERP: appropriate subparagraph or identification of other documents.

NOTE: Relevant information inappropriate for other parts of the VRDS.

FIGURE 1-1 VRDS FORM

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SW - Software and Computers

(2) Configuration Element Identifier [2 digits (alpha)]

MD - MiddeckGS - GSEER - EXPRESS RackTR - Transportation RackMP - MPLM

(3) Numerical Sequence NNN [3 digits (numeric)]

Use all digits - 001, 002, etc. This number represents sequential numbering of VRDSs driven by the discipline identifier and configuration element identifier (Example, ME-TR-002). This is the second VRDS within the mechanical discipline associated with the EXPRESS Transportation Rack.

B. Requirement Title

The requirement title is a category identification of the design-to requirement and is usually taken from the IDD requirement paragraph title where possible. If the verification requirement covers more than one IDD requirement, a general statement will be provided.

C. Verification Method

There are four unique methods of verifying a design requirement: Analysis (A), Test (T), Inspection (I), and Demonstration (D). Each VRDS will identify the required method of verification by indicating the method letter identifier, or a combination of identifiers, if more than one method applies.

(1) Analysis

Analysis is the technical evaluation process of using techniques and tools such as mathematical models and computer simulations, historical/design/test data, and other quantitative assessments to calculate characteristics and verify specification compliance. Analysis may be used to verify requirements where established techniques are adequate to yield confidence or where testing is impractical. Included in this category is analysis by similarity whereby a comparison is drawn to items previously verified to the same or more stringent criteria. A special type of analysis for payload experiments that have flown on previous Space Station missions is described in Recertification.

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(2) Test

Test is actual operation of equipment, normally instrumented, under simulated conditions or the subjection of equipment to specified environments to measure and record responses in a quantitative manner. Testing is the preferred verification method.

(3) Inspection

Inspection is a physical measurement or visual evaluation of equipment and associated documentation. Inspection may be used to verify construction features, drawing compliance, workmanship, and physical condition. It includes determination of physical dimensions.

(4) Demonstration

Demonstration is the qualitative determination of compliance to requirements by observation during actual operation or simulation under preplanned conditions and guidelines. Usually, no data is taken during a demonstration as is done for a test.

D. Hazard Report Number

This block will only appear in a VRDS that has a related safety requirement. It can be used by the PD as a cross reference to a particular Safety Hazard Report (SHR) number when appropriate.

1.2.2 VRDS Body

The body of the VRDS contains the following: a restatement of the applicable IDD design-to requirement; the associated verification method or reverification method description and tasks to be accomplished to verify the requirement has been satisfied; the data that must be generated and delivered as proof of meeting the requirement; and any applicable documentation and notes that may aid in accomplishing the verification.

A. Verification or Reverification Requirement

The IDD requirement paragraph number and a restatement of the IDD/ICD requirement that must be verified to ensure payload hardware/software interface compatibility and safety. If data is different for reverification, it will be defined here.

B. Description of Verification Method

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Instructions and details specifying how the verification method(s), as identified in the header, should be implemented (what analyses or tests are required and implementation details). In addition, any related clarification deemed necessary to further explain what is required will be provided. There is nothing different between the verification and reverification for methods.

C. Data Submittal Requirements

Verification and reverification data types are as follows:

(1) Certificate(s) of Compliance (COC) - This data type is a signed certificate(s) (see Appendix E) documenting the completion of all applicable verification requirements identified in the certificate. This COC is submitted by the PD in accordance with the program development schedule.

(2) Integrated Rack Analyses Data - This data type represents actual payload data required to support an integrated rack complement analysis to be performed by the ERO or data which must be forwarded to other integration organizations. This could include analysis reports, test reports and/or inspection results.

(3) Data Certification - A Data Certification is a memorandum from a PD certifying that the requirements identified on the referenced VRDS have been met and providing the required summary results. It should also state that the supporting data will be maintained by the PD and provided upon request.

Data submittals for initial verification as well as reverification will be identified by template milestone related delivery dates. A single VRDS may have multiple data submittal types. Note: While all data generated during a PD’s verification is not required to be submitted, all data collected must be archived by the PD at the PD site for future reference if needed by the ISS program.

D. Applicable Documents and Notes

This section will be used to identify applicable documentation to assist the developer in accomplishing the specified verification requirements. The references will be detailed with specific paragraphs and/or sections referenced where possible. The specific revision or change identification is located in Section 2 of SSP 52000-PVP-ERP. This part of the VRDS will also contain additional notes and clarification that is inappropriate for other parts of the VRDS.

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1.3 EXCEPTIONS/EXCEPTION PROCESSING

Any exceptions to requirements defined in the payload-unique ICD or methods specified in the payload-unique PVP must be submitted under specific procedures and guidelines to assure proper control, evaluation and approval. The exception processing details are shown in Section 2.3.2 of the SSP 52000-PVP-ERP/IA. Exceptions are to be documented in Appendix A, Verification Deviation Tables.

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APPENDIX A

VERIFICATION DEVIATION TABLE

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APPENDIX A, VERIFICATION DEVIATION TABLE

Table a-I Verification Deviation Table

VDS NUMBER VDS TITLE DESCRIPTION OF DEVIATION REASON FOR DEVIATION

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APPENDIX B

VERIFICATION REQUIREMENT DEFINITION SHEETS

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ST-ER-001 Structural Strength A or A and T


Structural Integrity Verification Requirement:

1. The Payload Developer (PD) shall support the coupled loads analysis process by providing documented finite element models and/or mass properties data per SSP 52005, Section 7.1. Payloads hard mounted in an EXPRESS Rack during launch and/or landing shall provide a finite element model verified as required by SSP 52005, Table 7.1-1. Payloads transported in an EXPRESS Rack foam packed in a standard modular stowage locker or ISIS Drawer shall provide mass properties data only (weight, center of gravity, and mass moments of inertia). Payloads transported in the Middeck are exempt from this requirement. (4.6.1)

2. EXPRESS Rack payload structural design and verification for interface and safety considerations, including glass, window, and ceramic structures, shall be in accordance with the requirements specified in NSTS 1700.7 and ISS Addendum, NSTS 18798, and SSP 52005. Payload hardware shall be designed to maintain positive margins of safety during all mission phases. Design load factors shall be determined for transportation/ground-handling, lift-off, on-orbit, descent, landing, and emergency landing events. (3.4.3.6.2.1, 4.1.2, 4.2.1, 4.3.2, 4.5.2, 4.6.1, 4.7.1)

3. EXPRESS Rack payload lift-off loads shall include random vibration loads combined (in the same coordinate system) with the low frequency transient lift-off loads and other loads which apply during the launch phase using the methodology of SSP 52005, Section 4.1.2. Random vibration loads will be determined using the methodology of SSP 52005, Section 4.1.5 and the appropriate random vibration environment defined in the EXPRESS IDD, Section 4.3.2. (4.1.2, 4.3.2, 4.6.1)

4. All payloads susceptible to acoustic impingement (those with large surface areas or low mass density) shall be designed to withstand the Sound Pressure Levels (SPL) specified in Table 4-IX. Acoustic loads may be calculated per SSP 52005, Section C.1.4.1 and shall be combined with the random vibration and low frequency transient load factors using the root-sum-square method. (4.6.1, 4.7.1)

5. Payload equipment shall be designed to maintain positive margins of safety when exposed to on-orbit loads of 0.2 g’s acting in any direction during all on-orbit loading events. (4.5.2, 4.6.1)

6. The PD shall evaluate discrepancies between the design drawings and the as-built hardware and update the structural, mechanical, and dynamic analyses and/or tests as required to reverify the structural integrity if the change warrants. (4.6.1)

Description of Verification Method:

1. N/A2. Verify by stress analysis or stress analysis and test using appropriate factors of safety and design

load factors that all safety-critical structures (SCS) have positive margins of safety for all mission phases.

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VERIFICATION REQUIREMENT DEFINITION SHEET (CONTINUED)


ST-ER-001 Structural Strength A or A and T


Description of Verification Method: (Continued)

3. N/A4. Verify by inspection of the flight hardware to the drawings that the analysis and tests addressed

the as-built design. Update the analysis or analysis and tests to account for any significant discrepancies between the as-built hardware and the configuration analyzed/tested.

Required Verification Data:1. Structure Verification Plan (SVP) in accordance with SSP 52005

(submitted directly to the Structures Working Group (SWG) for approval during either the PD PDR or Phase O/1 Flight Safety Review but no later than the Phase O/1 Flight Safety Review).

2. Data certification that provides a summary of the margins of safety (can include load factors also) for design loads for all SCS identified in accordance with SSP 52005.

3. N/A4. N/A5. Data certification that the flight hardware conforms to the drawings and

with the analyzed/ tested design or revised analysis/test results based on the as-built design.

Data Submittal Dates:P/L PDR or L-20 mo

(reference only)

L-12 mo

L-3 mo


On-orbit relocation of the payload: No reverification required.


N/A


N/A


NSTS 1700.7, ISS Addendum: par 208.1NSTS 18798NSTS 21000-IDD-MDKSSP 52000-IDD-ERP: par 3.4.3.6.2.1, 4.1.2, 4.2.1, 4.3.2, 4.5.2, 4.6.1, 4.7.1SSP 52005: Entire Document

Notes:

1. EXPRESS Rack backplate interface force allowables are shown in EXPRESS IDD Table 3-I.

2. Acoustic loading is already included in the random vibration load factors defined for EXPRESS Rack mounted payloads (ref SSP 52005, Section 4.1.7).

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ST-ER-002 Crew-Applied Loads A



Payload equipment shall be designed to maintain positive margins of safety when exposed to the crew-induced loads defined in Table 4-VIII of the IDD. (4.5.1, 4.6.1)


Verify the capability of all equipment that has a potential interface with the crew for operation, use, or impact (whether inadvertent or not) to withstand crew-applied loads as defined in Table 4-VIII of the EXPRESS IDD. Verify by stress analysis, using appropriate factors of safety from SSP 52005, Table 5.1.2-1, that all structures have positive margins of safety.


Data Certification providing a summary listing of all operational modes analyzed and a summary of the margins of safety.


L-12 mo




N/A


N/A


NSTS 1700.7, ISS Addendum: par 208.1SSP 50005: par 8.8.3.3B, 11.4.3.DSSP 52000-IDD-ERP: par 4.5.1, 4.6.1SSP 52005: par 4.1.8, 5.1.2

Note: Requirements are different between the middeck and the ISS (see ST-MD-003).

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ST-ER-003 On-Orbit Depress/Repress A or A and T



Payload structures containing trapped volumes shall maintain positive margins of safety per NSTS 1700.7 and ISS Addendum, NSTS 18798, and SSP 52005 when exposed to the worst-case applicable depressurization/repressurization environment defined in the EXPRESS IDD, Section 4.8 and Table 5-I, and the Middeck IDD, Section 6.1. (4.6.1, 4.8.1, 4.8.3)

Description of Verification Method:Determine by analysis or analysis and test that all payload equipment structures containing trapped volumes have positive margins of safety for appropriate carrier/module minimum and maximum pressures. Otherwise, perform a venting analysis to determine worst-case positive and negative pressure differentials under worst-case depress/repress conditions and perform structural analysis to show positive margins of safety, including negative pressure collapse stability, at these worst-case pressures.


Certificate of Compliance (COC)


L-4.5 mo




N/A


N/A


NSTS 1700.7, ISS Addendum: par 208NSTS 18798SSP 21000-IDD-MDKSSP 52000-IDD-ERP: par 4.6.1, 4.8.1, 4.8.3, Table 5-ISSP 52005: par 4.1.12

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ST-ER-005 Acoustic Emission Limits T


Acoustic Verification Requirement:

Payload equipment-generated acoustic noise levels shall not exceed specified values. (4.7.2.2, 4.7.2.2.1, 4.7.2.3, 4.7.2.4)


1. Continuous Acoustic Noise - Verify that the payload (including PD-provided active ancillary equipment operated outside the rack) does not exceed the continuous acoustic noise requirements specified in the IDD. Any independently operated ancillary equipment item, stowed within the rack or elsewhere, and deployed on-orbit for a separate function other than that of the rack system, shall individually comply with the requirements. Continuous noise sources which exhibit intermittent acoustical characteristics must meet both the continuous noise specification and the intermittent noise requirements of paragraph B below.Verification of continuous noise sources shall be performed by test. Sound Pressure Level (SPL) test measurements shall be made for each serialized payload (or ancillary equipment operated outside the rack) following the guidelines provided in Appendix H in the Instruction Annex. The SPL test shall use a Type 1 Sound Level Meter to measure the SPL at the loudest location 2 ft (0.6 m) from each payload face, e.g., front, rear, top, bottom, left, and right. SPL shall be measured in each of eight octave bands: 63 Hz, 125 Hz, 250 Hz, 500 Hz, 1000 Hz, 2000 Hz, 4000 Hz, and 8000 Hz. Verification shall be considered successful when the test shows that the loudest noise does not exceed the levels specified in the IDD. In addition to SPL measurements, payloads are required to take sound power measurements following the guidelines provided in Appendix H in the Instruction Annex.

2. Intermittent Acoustic Noise - Verify that the payload (including PD-provided active ancillary equipment operated outside the rack) does not exceed the intermittent acoustic noise requirements specified in the IDD. Any independently operated ancillary equipment item, stowed within the rack or elsewhere, and deployed on-orbit for a separate function other than that of the rack system, shall individually comply with the requirements. Intermittent noise characteristics shall be quantified in terms of (1) when the intermittent sound occurs, (2) duration and A-weighted SPL, and (3) a projected mission timeline(s). Intermittent noise sources which also exhibit continuous acoustical noise characteristics must meet both the intermittent noise requirements and the continuous noise specification of paragraph A above.Verification of intermittent noise sources shall be performed by test. Overall A-weighted SPL (dBA) test measurements shall be made for each serialized payload (or ancillary equipment operated outside the rack) following the guidelines provided in Appendix H in the Instruction Annex. The SPL test shall use a Type 1 Sound Level Meter to measure the overall A-weighted SPL (dBA) at the loudest location 2 ft (0.6 m) from each payload face, i.e., front, rear, top,

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ST-ER-005 Acoustic Emission Limits T



bottom, left, and right. Verification shall be considered successful when the test shows that the overall A-weighted SPL (dBA) does not exceed the levels specified in the IDD.


1. Acoustic Control Plan for Items 1 and 2.

2. Preliminary acoustic summary that includes a list of potential noise sources (continuous and intermittent) and their locations.

A. Continuous Noise Source - SPL (dB) for the eight octave bands (for each serialized unit). (Note: Sound power level data must also be provided for the eight octave bands).

B. N/A

3. Final submittal of A and B data listed below:

A. Continuous Noise Source - SPL (dB) for the eight octave bands (for each serialized unit). (Note: Sound power level data must also be provided for the eight octave bands).

B. N/A

Data Submittal Dates:L-22 mo

L-20 mo

L-9.5 mo (with further updates as required.)


On-orbit relocation of the payload. No reverification required.


N/A


N/A


SSP 50005: par 5.4SSP 52000-IDD-ERP: par 4.7.2.2, 4.7.2.2.1, 4.7.2.3, 4.7.2.4

Note: Requirements are different between the middeck and the ISS. (See ST-MD-004)

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ST-ER-007 Ground Transportation Loads A



1. Payloads which have the potential to create a flight safety hazard if damaged during handling and transportation (including fracture-critical parts or components) shall be analyzed in accordance with SSP 52005 using the transportation limit load factors defined in EXPRESS IDD Table 4-XII. (4.9.1)

2. Payloads which have the potential to create a flight safety hazard if damaged during handling and transportation (including fracture-critical parts or components) shall be analyzed, in accordance with SSP 52005, for the drop requirements defined in FED-STD-101, Method 5005.1, 5007.1, or 5008.1. (4.9.2)

3. Ground transportation analyses shall evaluate the flight hardware in the shipping configurations. (4.9.1, 4.9.2)

4. Handling attach points for flight hardware shall be designed to ensure positive margins of safety during handling events defined in KHB 1700.7. (4.6.1)


1. Verify by analysis of the payload design that all payloads which have the potential to create a flight safety hazard if damaged during handling and transportation have positive margins of safety when exposed to the ground handling loads defined in the EXPRESS IDD in the shipping configurations.

2. Verify by analysis of the payload design that all payloads which have the potential to create a flight safety hazard if damaged during handling and transportation have positive margins of safety when exposed to the drop requirements defined in FED-STD-101, Methods 5005.1, 5007.1, or 5008.1 in the shipping configurations.

3. Verify by analysis of the payload design that handling attach points for flight hardware have positive margins of safety during handling events defined in KHB 1700.7.




L-4.5 mo


On-orbit relocation of payload. No reverification required.


N/A


N/A

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ST-ER-007 Ground Transportation Loads A



NSTS 1700.7, ISS Addendum: par 208SSP 52000-IDD-ERP: par 4.6.1, 4.9.1, 4.9.2SSP 52005: par 4.1.11, 5.1.4

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ST-ER-008 Fracture Control A and I


Structural Integrity Verification Requirement:Payload structural components, including all pressure vessels, the failure of which would cause damage to the Orbiter, damage to the ISS, or injury to personnel, shall be analyzed to preclude failures caused by propagation of pre-existing flaws. Payload Safety Critical Structure and components which are classified as Fracture Critical in SSP 52005B, shall meet fracture control requirements specified in SSP 52005B and NASA-STD-5003.Fracture control documentation of critical structural components shall be processed by the PD in accordance with NSTS 1700.7 and its ISS Addendum, NSTS 13830, NSTS 18798 (including JSC Letter TA-94-057, “Modified Fracture Control Criteria and Guidelines for Payloads”), NASA-STD-5003, and SSP 52005 during the payload safety review process. (4.6.2)

Description of Verification Method:Generate a Fracture Control plan (FCP) which meets SSP 52005B Sections 5.0, 5.3 and NASA-STD-5003 requirements and which is approved by the PSRP. The FCP shall assign fracture control responsibility within the PD organization and describe the PD fracture control implementation processes to be followed per SSP 52005B and NASA-STD-5003 requirements including activities such as: materials selection, design, classification, analysis, traceability, documentation, fabrication, testing, verification, inspection, discrepancy disposition and transportation.Perform a screening of payload parts per the requirements of SSP 52005B sections 3.x, 5.x, and 9.3.2.1 to classify all structure and components. Structure and components classified as fracture critical shall meet all fracture control requirements including analysis and testing as specified in SSP 52005B, Sections 6.2.x, 7.5.2, and NASA-STD-5003.Provide final documentation in the Fracture Control Summary Report, which describes the classification of all payload structure and components, and the disposition of all fracture critical hardware per SSP 52005B, Sections 6.2.11 and 9.3.2.6 requirements.


1. Fracture Control Plan (submitted to the PSRP for approval during the Phase 0/1 Flight Safety Review).

2. Fracture control status, including parts categorization (submitted to the PSRP during Phase 2 Flight Safety Review).

3. Data Certification providing a fracture control summary report (submitted to the PSRP during the Phase 3 Flight Safety Review).


L-20 mo (Ref. Only)

Delete Requirement

L-11.5 mo



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ST-ER-008 Fracture Control A and I



N/A


N/A


NASA-STD-5003, Entire DocumentNSTS 1700.7, ISS Addendum: par 208NSTS 13830NSTS 18798 (including JSC Letter TA-94-057)NSTS 21000-IDD-MDK

SSP 52000-IDD-ERP: par 4.6.2SSP 52005, Entire Document

Note: Related VRDSs: ST-ER-001, ST-ER-004

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ST-ER-009 Securing of Threaded Fasteners A and I or T



1. Threaded fasteners connecting safety-critical structures shall use a means of positive locking. (3.4.5)

2. Fracture critical threaded fasteners (and threaded fasteners used in an application of retaining a fracture-critical rotating device) shall be safety cabled or cotter pinned. If on-orbit removal is not required, safety wire can be used. (3.4.5.1)

3. Redundant threaded fasteners (non-fracture critical) in habitable areas or removable on-orbit shall employ self-locking threaded devices or approved locking compounds. (3.4.5.2A)

4. Self-locking threaded devices shall meet the requirements of MIL-STD-1312-7 (or equivalent). (3.4.5.2B)

5. Locking compounds shall be selected from MSFC-HDBK-527/JSC-09604 (or equivalent). (3.4.5.2C)

6. Locking compounds shall not be used in areas where excess compound could migrate to surfaces which must remain free to move. (3.4.5.2D)

7. Self-locking devices which can generate debris shall be avoided in applications where particulate contamination may cause damage or degradation to the equipment or vehicle. (3.4.5.2E)

8. Redundant threaded fasteners (non-fracture critical) not in a habitable area and not removable on-orbit shall employ safety wire, safety cable, cotter pins, built-in self-locking features, or approved thread-locking compounds. (3.4.5.2F)

9. Safety wires shall not be used on fasteners which must be removed on-orbit. (3.4.3.6.4)

10. All safety-critical fasteners shall be torqued in accordance with MSFC-STD-486 and analyzed to the requirements defined in NSTS 08307. (4.6.1)

Notes:

1. Payload fasteners internal to payload enclosures, attaching internal components shown to be contained if released (per SSP 52005, Sections 5.3.1.2 and 6.2.1), are excluded from this requirement.

2. Vibration testing (to flight levels or higher in accordance with SSP 52005, Section 7.2.2) demonstrating that fasteners do not loosen may be used to satisfy requirement parts 1, 3, and 8.

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1. Verify by inspection of the payload design that all fasteners connecting safety-critical structures use a means of positive locking, have been proven secure through vibration testing, or attach internal components shown by analysis to be contained if released.

2. Verify by inspection of the payload design that fracture critical threaded fasteners (and threaded fasteners retaining a fracture-critical rotating device) are safety cabled or cotter pinned or, if on-orbit removal is not required, safety wired.

3. Verify by inspection of the payload design that all redundant threaded fasteners (non-fracture critical) in habitable areas or removable on-orbit employ self-locking threaded devices or approved locking compounds, have been proven secure through vibration testing, or attach internal components shown by analysis to be contained if released.

4. Verify by inspection of the payload design that self-locking threaded devices meet the requirements of MIL-STD-1312-7 (or equivalent).

5. Verify by inspection of the payload design that locking compounds are selected from MSFC-HDBK-527/JSC-09604 (or equivalent).

6. Verify by inspection of the payload design that locking compounds are not used in areas where excess compound could migrate to surfaces which must remain free to move.

7. Verify by inspection of the payload design that self-locking devices which can generate debris are not used in applications where particulate contamination may cause damage or degradation to the equipment or vehicle.

8. Verify by inspection of the payload design that redundant threaded fasteners (non-fracture critical) not in a habitable areas and not removable on-orbit employ safety wire, safety cable, cotter pins, built-in self-locking features, or approved thread-locking compounds, or have been proven secure through vibration testing, or attach internal components shown by analysis to be contained if released.

9. Verify by inspection of the payload design that safety wires are not used on fasteners which must be removed on-orbit.

10. A. Verify by inspection of the payload design that all safety-critical fasteners are torqued in accordance with MSFC-STD-486.

B. Verify by inspection of the payload structural analysis that all safety-critical fasteners are analyzed to the requirements defined in NSTS 08307.

B-12

SSP 53074-PVP, Draft 16/28/02








L-4.5 mo




N/A


N/A


MS 33540SAE AS4536SSP 52000-IDD-ERP: par 3.4.3.6.4, 3.4.5, 3.4.5.1, 3.4.5.2A-F, 4.6.1SSP 52005: par 5.6, 7.2.2

B-13

SSP 53074-PVP, Draft 16/28/02



ST-ER-010 Pressurized Systems A and/or T



The structural integrity of all pressure system components, including lines and fittings, pressure tanks, actuating cylinders, valves, filters, and switches, shall be maintained.


1. Pressure Vessels - Any component that meets the criteria of a pressure vessel (as specified in NSTS 1700.7 ISS Addendum) shall be verified by stress analysis, burst test, and proof test using appropriate factors of safety (as specified in SSP 52005, paragraph 5.1.3.2) to show positive margins of safety. Appropriate combinations of load factors (as specified in SSP 52005, paragraph 4.1.6) shall be used. Components meeting the criteria of a pressure vessel are deemed fracture-critical and must also satisfy verification item ST-ER-008, “Fracture Control.”

Paragraph 6.2.3 of SSP 52005 describes the specific analysis, test, and unique requirements for qualifying/verifying a pressure vessel. Applicable combination of loads environments (as specified in SSP 52005, paragraph 4.1.6) shall be used. (4.1.2, 4.2.1, 4.3.2, 4.6.1)

2. Components Not Meeting Criteria of Pressure Vessel - Verify by stress analysis and/or burst test using factors of safety as specified in NSTS 1700.7 ISS Addendum, paragraph 208.4c, that pressure system components not meeting the criteria of a pressure vessel have positive margins of safety. Appropriate combinations of load factors (as specified in SSP 52005, paragraph 4.1.6) shall be used. Certified vendors burst data may be used in lieu of analysis to verify margins of safety when pressure loads are the principal failure mode (except for attachment lugs/fittings, which still must be verified by analysis to show capability of withstanding flight loads). A pressurized system is considered fracture-critical if leakage or loss of pressurization would result in a catastrophic hazard (as specified in SSP 52005, paragraph 6.2.4). In that case, the system would also be required to satisfy verification item ST-ER-008, “Fracture Control.”

Note: The verification of payload hardware shall be compliant to the water coolant system MDP requirements specified in the IDD, paragraph 5.3.1.5.11. The MDP of payload volumes connected to the TCS system shall be verified by the test and analysis guidelines identified in SSP 52005, paragraph 6.2.4. (4.1.2, 4.2.1, 4.3.2, 4.6.1)

3. Pressure system components which perform a Hazard Control Safety Function (e.g. relief values) shall either be qualified to maintain their function over the entire life of the payload or be periodically reverified on-orbit or replaced on-orbit with qualified components. If reverification or replacement on-orbit is planned the payload design shall allow the safe access by the crew.

B-14

SSP 53074-PVP, Draft 16/28/02



ST-ER-010 Pressurized Systems A and/or T



Data identified for Phase II Flight Safety Review Data Package in accordance with SSP 52005, Table 9.2.2-1.

Data identified for Phase III Flight Safety Review Data Package in accordance with SSP 52005, Table 9.2.2-1.


L-20 mo (Ref. Only)

L-11.5 mo


1. On-orbit relocation of the payload: No reverification required.

2. Payloads remaining on-orbit past the original period of certification of the safety features or inhibits must perform a re-verification of the activities as identified in Part 3 of the “Description of the Verification Method” identified above.

This is the reverification requirement for safety features as per NSTS 18798B, MA2-98-135. It covers not only items that are limited operating life items (i.e., batteries, seals, etc.) but also items such as micro-switches, PRVs, etc., that perform the safety control function for a payload hazard.


1. N/A

2. Same as “Required Verification Data” identified above.


N/A


NSTS 1700.7, ISS Addendum: par 208.4NSTS 21000-IDD-MDKSSP 52000-IDD-ERP: par 4.1.2, 4.2.1, 4.3.2, 4.6.1SSP 52005: par 4.1.6, 4.1.10.1, 4.1.12, 5.1.3, 5.1.3.2, 5.1.3.3, 5.1.3.4, 5.1.3.6, 6.2.3, 6.2.3.4, and Table 9.2.2-1

Note: Related VRDSs: ST-ER-008

B-15

SSP 53074-PVP, Draft 16/28/02



ST-ER-011 Weight and Center of Gravity A and T



1. N/A

2. The weight-to-CG relationship for single or double MDL payloads attached to the EXPRESS Rack baseplate shall conform to Table 4-VII in the EXPRESS IDD. (4.4.1, 4.4.2)

3. N/A

4. The weight-to-CG relationship for payloads attached to the middeck wire trays shall conform to NSTS 21000-IDD-MDK, Figures 4.8.2-1 or 4.8.2-2.

Description of Verification Method:1. Determine by test the actual weight of each payload element in the launch and landing

configurations, including cables, loose or removable equipment (e.g., film or stowage items). Allowable tolerance of measurement accuracy shall be 0.10 lb or 0.3 percent, whichever is greater.

2. Determine by test the actual CG of each payload element in three orthogonal axes. The coordinate system used shall be clearly defined in the weight and balance report and shall be parallel with the payload coordinate system defined in SSP 52000-IDD-ERP, Figure 3-2. Allowable tolerance for CG measurement accuracy shall be 0.25 in. in all three axes.

3. Determine by analysis and provide moments and products of inertia (negative integrals) about the identified axis system used for the CG location.

4. Verify by test that the actual mass is no greater than the control mass and the CG location is within specified location envelopes (if applicable).

All flight items shall be accounted for (i.e., fluids, gasses, foam, miscellaneous hardware, etc.).


Certified weight and balance report for each payload element. This data is necessary for the integrated rack payload analyses.


L-12 mo (see notes)




N/A


N/A

B-16

SSP 53074-PVP, Draft 16/28/02



ST-ER-011 Weight and Center of Gravity A and T




NSTS 21000-IDD-MDK: par 4.8SSP 52000-IDD-ERP: par 4.4.2Notes:

1. For payloads requiring late load activities, the final as weighed test results are performed at the launch site prior to loading in the Orbiter; however, analytical data must be submitted per the above schedule.

2. A payload element is defined as a logical grouping of flight hardware. Each Middeck Locker (MDL), ISIS drawer, or part that is transported separately is a payload element. In general, a part or assembly that is handled, transported, or installed separately should be considered a payload element. EXPRESS payloads are to be verified at the experiment/box level as a payload element.

B-17

SSP 53074-PVP, Draft 16/28/02



ST-ER-012 Portable Fire Extinguisher (PFE) Discharge Rate A



Payload equipment which has a PFE access port shall maintain positive margins of safety when exposed to the PFE discharge rate (i.e., pressurization) given in Figure 4-3 of the EXPRESS IDD. (4.8.4)


Perform an analysis which determines the maximum delta pressure from within to outside the payload equipment during PFE discharge and shows that the payload equipment maintains positive margins of safety when exposed to this maximum delta pressure.




L-4.5 mo




N/A


N/A


NSTS 1700.7, ISS Addendum: par 208SSP 52000-IDD-ERP: par 4.8.4SSP 52005: par 4.1.12

B-18

SSP 53074-PVP, Draft 16/28/02



ST-MD-001 Orbiter/Middeck Attach Point Provisions A



The attachment points on the payload mounting structure for securing to a single or double adapter plate, PMP, or VPMP in the Orbiter/middeck shall be designed per Figure 3-15 in the EXPRESS IDD. (3.4.3.6.1)


Perform an analysis of the payload design to verify that the attach points on the payload mounting structure are designed per Figure 3-15 in the EXPRESS IDD.




L-4.5 mo




N/A


N/A


NSTS 21000-IDD-MDKSSP 52000-IDD-ERP: par 3.4.3.6.1

B-19

SSP 53074-PVP, Draft 16/28/02



ST-MD-002 MDK Natural Frequency A or T


Structural Integrity Middeck Verification Requirement:

Middeck payloads not stowed in a middeck locker shall have natural frequencies greater than 30 Hz with respect to their Orbiter attachment interface. (4.1.1)


The natural frequencies shall be determined by analysis or by dynamic testing (modal survey or vibration test). In the analysis, standard engineering calculations may be utilized, if appropriate, or, preferably, a finite element computer model may be utilized following the methodology given in SSP 52005. If verification is by test, the test must consider lift-off and landing configurations and must include adequate instrumentation to identify all primary structural modes.




L-4.5 mo




N/A


N/A


NSTS 21000-IDD-MDK: par 4.1SSP 52000-IDD-ERP: par 4.1.1SSP 52005: par 5.7, 6.1.1.2, 6.1.1.3, 6.1.1.4.1, 7.2.1

Note: This requirement is different in the ISS MPLM.

B-20

SSP 53074-PVP, Draft 16/28/02



ST-MD-003 MDK Crew-Applied Loads A or A and T


Structural Integrity Middeck Verification Requirement:

Payload-provided middeck equipment shall be designed for a 125 pound limit load distributed over a 4 inch x 4 inch area. (4.5.1)


Determine by stress analysis, the capability of all equipment that has a potential interface with the crew for operation, use, or impact (whether inadvertent or not) to withstand the crew-applied loads without surface penetration or failure of safety-critical structural items.




L-4.5 mo




N/A


N/A


NSTS 1700.7, ISS Addendum: par 208NSTS 21000-IDD-MDK: par 4.4SSP 52000-IDD-ERP: par 4.5.1

Note: This requirement is different in the ISS (see ST-ER-002).

B-21

SSP 53074-PVP, Draft 16/28/02



ST-MD-004 MDK Acoustic Levels T


Acoustics Middeck Verification Requirement:

1. Individual middeck payloads shall not emit continuous acoustic noise into the crew working/living spaces exceeding the level shown in Figure 4.7.3.1-2 of the Middeck IDD, as measured one foot from the noise radiating surface(s). (4.7.2.2, 4.7.2.2.1)

2. Maximum noise levels for intermittent noise generated by middeck payloads shall meet the limits of NASA-STD-145A in NSTS 08080-A. (4.7.2.2, 4.7.2.2.1)

Description of Verification Method:Verify by test that the payload-generated acoustic levels do not exceed specified values.




L-4.5 mo


On-orbit relocation of the payload to the ISS. Payload must meet requirements of ST-ER-005.


See ST-ER-005


See ST-ER-005


NSTS 21000-IDD-MDK: par 4.7.3, 4.7.4.1, 4.7.4.2, 4.7.4.3, 4.7.4.4, 4.7.4.5, 4.7.4.6SSP 52000-IDD-ERP: par 4.7.2.2, 4.7.2.2.1

Note: This requirement is different in the ISS (see ST-ER-005).

B-22

SSP 53074-PVP, Draft 16/28/02



ME-ER-001 EXPRESS Mounting Plates I


Mechanical Verification Requirement:

Single, double, or quad middeck locker equivalent payloads shall be compatible with the mechanical interfaces defined in Figure 3-5 and 3-5A of the EXPRESS IDD. (3.4.1.1)


Perform an inspection of the flight hardware to show compliance with the mechanical interface defined in the EXPRESS IDD.




L-4.5 mo




N/A


N/A


SSP 52000-IDD-ERP: par 3.4.1.1

Note: Payloads launched in the 8/2 EXPRESS Rack must restrict themselves to either a single or double MDLE configuration. Quad MDLE payloads must be launched in the EXPRESS Transportation Rack (ETR).

B-23

SSP 53074-PVP, Draft 16/28/02



ME-ER-003 PD-Supplied Locker Requirements A and I


Mechanical Verification Requirement:All PD supplied lockers shall use the latches defined in Section 3.4.2.6A of the EXPRESS IDD. (3.4.2.6A)


Perform an inspection of the flight hardware to verify that the proper latches are used.




L-4.5 mo




N/A


N/A


NSTS 1700.7, ISS Addendum: par 208SSP 52000-IDD-ERP: par 3.4.2.6ASSP 52005

B-24

SSP 53074-PVP, Draft 16/28/02



ME-ER-004 Mounting Panels I



1. Payloads installed on mounting panels using STS provided fasteners shall have a baseplate thickness of 0.25 inches. (3.4.3)

2. N/A

3. N/A

4. N/A

5. Payloads installed directly onto a PMP or two PMPs shall not protrude more than 20.562 inches along the Xpl axis from the face of the PMP. (3.4.3.3)

6. N/A

7. N/A

8. N/A


1. Verify by inspection of the flight hardware that payloads installed on mounting panels using STS-provided fasteners have a baseplate thickness of 0.25 inches.

2. N/A

3. N/A

4. N/A

5. Verify by inspection of the flight hardware that payloads installed directly onto a PMP or two PMPs do not protrude more than 20.562 inches along the Xpl axis from the face of the PMP.

6. N/A

7. N/A

8. N/A




L-4.5 mo



B-25

SSP 53074-PVP, Draft 16/28/02



ME-ER-004 Mounting Panels I



N/A


N/A


NSTS 21000-IDD-MDK: par 3.4.2.1, 3.4.2.2, 3.4.2.3SSP 52000-IDD-ERP: par 3.4.3, 3.4.3.3

B-26

SSP 53074-PVP, Draft 16/28/02



ME-ER-005 On-Orbit Separation Interface Requirements I


Mechanical Verification Requirement:1. EXPRESS Rack payloads transported in the Orbiter middeck shall be designed to interface with

the SSP mounting panels. (3.3.1.2)2. On-orbit separation interface shall be between EXPRESS Rack payloads transported in the

Orbiter middeck and the single or double adapter plates, PMP, or VPMP. (3.4.3.5.1A)3. Payloads shall be designed to allow access to the payload mounting bolts as defined in SSP

52000-IDD-ERP, paragraphs 3.4.3.6 through 3.4.3.6.3. (3.4.3.5.1B)4. Payload equipment shall not require the use of special tools for payload removal unless the tool

is supplied by the PD. (3.4.3.5.1C)

Description of Verification Method:1. Verify by inspection of the payload design that the payload is compatible with the interface and

envelope requirements of the intended adapter plate or mounting panel.2. Verify by inspection of the payload design that the payload can be removed from the intended

adapter plate or mounting panel on-orbit.3. Verify by inspection of the payload design that the payload allows access to the payload

mounting bolts on-orbit per the EXPRESS IDD.4. Verify by inspection of the payload design that any special tool required for payload removal and

installation is provided by the EXPRESS IDD.


Category 1: Certificate of Compliance (COC) with the requirement.


L-4.5 mo (Note 1)




N/A


N/A


SSP 52000-IDD-ERP: par 3.3.1.2, 3.4.3.5.1A-C

Notes:1. Delivery date assumes 30 days prior to turnover to KSC, and PD hardware must be turned

over to KSC at L-5 months.2. PDs are encouraged to use standard metric/English fasteners and tools.3. See related VRDS HF-ER-133 (part 8) for clearances.

B-27

SSP 53074-PVP, Draft 16/28/02



ME-ER-006 EXPRESS Rack Backplate A and I



1. The attachment points on the payload mounting structure for securing to the EXPRESS Rack backplate shall be designed per Figure 3-16 of the EXPRESS IDD. (3.4.3.6.2)

2. The interface ultimate force allowables shown in Table 3-I of the EXPRESS IDD shall be used in the structural analyses/assessment of the EXPRESS Rack backplate interface. (3.4.3.6.2.1)

3. The maximum dimension from the backplate surface to the GSE boss fittings on the ISPR portion of the EXPRESS Rack is 24.6 inches. Payloads that are transported only in EXPRESS Racks or transportation racks shall stay within this envelope. (3.4.3.6.2.2)


1. Perform an analysis of the payload design or inspection of the flight hardware to verify that the attachment points on the payload mounting structure are designed per the IDD.

2. Perform an inspection of the payload analysis to verify that the interface ultimate force allowables shown in Table 3-I are used in the structural analysis/assessment of the EXPRESS Rack backplate interface.

3. Perform an analysis of the payload design or inspection of the as-built hardware to verify that the payload stays within the IDD envelope.

Note: The 24.6 inch dimension includes all parts of the payload (i.e., cables, lines, connectors, QDs, switches, etc.).




L-4.5 mo




N/A


N/A


SSP 52000-IDD-ERP: par 3.4.3.6.2, 3.4.3.6.2.1, 3.4.3.6.2.2

Note: It is recommended that the threaded inserts be utilized in lieu of the sleeve bolt attachment points on the EXPRESS Rack backplate when the additional load carrying capability is required.

B-28

SSP 53074-PVP, Draft 16/28/02



ME-ER-007 Fastener Requirements A and/or I



The payload provides all interface fasteners which attach payload equipment to orbiter-provided mounting plates (single adapter plate, double adapter plate, PMP, VPMP) or to the EXPRESS Rack or EXPRESS Transportation Rack (ETR) backplates. These interface fasteners shall meet the requirements in Table 3-II and Figure 3-16. (See Note 3 below.) (3.4.3.6.3)


Perform an analysis and/or inspection of the as-built flight hardware to verify the PD-provided attachment fasteners meet all of the requirements in Table 3.4.3.6.3-X and Figure 3-16 of the EXPRESS Rack IDD.




L-4.5 mo




N/A


N/A


SSP 52000-IDD-ERP: par 3.4.3.6.3

Notes:

1. Any fracture-critical fasteners required to be removed on-orbit and/or replaced must be safety cabled or cotter pinned.

2. Also see VRDS HF-ER-033.3. Modification of non-captive fasteners to incorporate a captive feature must be approved by

the Structures Working Group (SWG). For all interface bolts to be considered (analytically) to share carrying shear loads to the backplate the total radial clearance at each bolt must not exceed clearance fit requirements.

B-29

SSP 53074-PVP, Draft 16/28/02



ME-ER-009 Payload Static Envelopes A or I



Payload hardware design must not violate the static envelope dimensions shown in the following figures in the EXPRESS IDD:

1. N/A

2. MDLs or MDL replacement payloads envelope shall be as shown in Figures 3-5, 3-6, 3-9, 3-10, 3-11, 3-12, 3-13, and 3-14 (as applicable). (3.6.1B)

3. MDL replacement item attachment hardware envelope shall be as shown in Figures 3-5, 3-9, 3-10, 3-11, 3-12, 3-13, and 3-14 (as applicable). (3.6.1C)

Description of Verification Method:Perform an analysis of the payload design or inspection of the flight hardware to verify that the payload does not violate the static envelope dimensions.




L-4.5 mo




N/A


N/A


NSTS 21000-IDD-MDK: par 3.4.2.1, 3.4.2.2, 3.4.2.3, 3.4.2.4, 3.7SSP 52000-IDD-ERP: par 3.6.1B-C

B-30

SSP 53074-PVP, Draft 16/28/02



ME-ER-010 Pressure Relief Device Location A and I


Thermal Verification Requirement:

Subrack payloads shall not have a pressure relief device on the front of the subrack payload. (3.6.4)


Verification shall be by analysis of hardware design drawings (showing that there are no pressure relief devices on the front of the subrack payload) and then inspection that the as-built hardware complies with the drawings.




L-5 mo


N/A


N/A


L-5 mo


SSP 52000-IDD-ERP: par 3.6.4

B-31

SSP 53074-PVP, Draft 16/28/02



EL-ER-001 Voltage Levels T


Electrical Verification Requirement:

Payloads shall be compatible with the interface voltage levels as shown in the IDD figure. This figure is applicable at current ranges of 1.0 to 20.0 A. This figure is applicable to turn “ON” and turn “OFF” events. (6.2.1.1)


Verify by test that the payload is compatible with the interface voltage levels as shown in the IDD figure.




L-4.5 mo


1. On-orbit subrack PL changeout (new, reflight, or series) of the integrated rack: Same as the “Required Verification Data” identified above.

2. Payloads remaining on-orbit past the original period of certification of the safety features or inhibits must perform a re-verification of the activities as identified in the “Description of the Verification Method” identified above.



1. Certificate of Compliance (COC)



L-4.5 mo



Note: The Suitcase Simulator (ScS) does not provide a flight-like simulation of the EXPRESS Rack Solid-State Power Controller Module (SSPCM) power output.

B-32

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EL-ER-003 Reverse Current/Energy A



1. The payload shall comply with the reverse current limitation requirements described in the IDD. (6.2.1.3)

2. The payload shall comply with the reverse energy limitation requirements described in the IDD. (6.2.1.4)


1. Reverse current is defined as the current flowing into a Solid-State Power Controller Module (SSPCM) power output from an external source of energy.Verify by analysis that the reverse current requirement specified in the IDD is met.

2. Reverse energy is defined as the energy flowing into an a SSPCM power output from an external source of energy.Verify by analysis that the reverse energy requirement specified in the IDD is met. This requirement can also be satisfied when the analysis shows that the payload’s input is capacitive and <50 F/A of the SSPC rated output current setting.


Signed analysis report.


L-10 mo


1. On-orbit subrack PL changeout: Same as the “Required Verification Data” identified above.




Same as “Required Verification Data” identified above.


L-4.5 mo

Applicable Documents and Notes:SSP 52000-IDD-ERP: par 6.2.1.3, 6.2.1.4

B-33

SSP 53074-PVP, Draft 16/28/02



EL-ER-005 Overload Protection Device I or A



1. The payload shall provide an overload protection device in the power input lines. (6.2.2.1)

2. A payload overload protection device shall not be accessible without opening a door or cover, except that an operating handle or operating button of a circuit breaker, the cap of an extractor-type fuse holder, and similar parts may project outside the enclosure. (6.2.2.1.1)

3. A payload overload protection device (fuses and circuit breakers) intended to be manually replaced or physically reset on-orbit shall be located where they can be seen and replaced or reset without removing other components. (6.2.2.1.2)

4. Each payload overload protection device (fuse or circuit breaker) intended to be manually replaced or physically reset on-orbit shall be readily identified or keyed for its proper value. (6.2.2.1.3)

5. N/A


1. Verify by inspection of payload hardware or analysis that the payload has an overload protection device in the power input lines.

2. Verify by inspection of payload hardware or analysis that the payload overload protection device is not accessible without opening a door or cover except as described in the IDD.

3. Verify by inspection of payload hardware or analysis that the payload overload protection device (fuses and circuit breakers) intended to be manually replaced or physically reset on-orbit are located where they can be seen and replaced or reset without removing other components.

4. Verify by inspection of payload hardware or analysis that the payload overload protection device (fuse and circuit breaker) intended to be manually replaced or physically reset on-orbit is readily identified or keyed for its proper value.

5. N/A




L-4.5 mo



B-34

SSP 53074-PVP, Draft 16/28/02



EL-ER-005 Overload Protection Device I or A


Description of Reverification Requirements: (Continued)




1. COC



L-4.5 mo


SSP 50005: par 6.4.3.12B, 6.4.3.12C, 6.4.3.12D, 6.4.3.12ESSP 52000-IDD-ERP: par 6.2.2.1, 6.2.2.1.1, 6.2.2.1.2, 6.2.2.1.3, 14.1.3 (refers to 6.2.2)

B-35

SSP 53074-PVP, Draft 16/28/02



EL-ER-006 Current Limiting T or A



1. Each power output of the SSPCM will limit the current within 100.0 µs of an over current to a value less than the maximum current limit value as depicted in the IDD figure. The payload equipment shall be compatible with this specification. (6.2.3A)

2. The SSPC will activate to a resistive load sized for the rated output current or a capacitive load of 50 µF/A of rated output current. The payload equipment shall be compatible with this specification. (6.2.3B)

3. Payload electrical power distribution circuitry shall be designed in accordance with NASA Technical Memorandum (TM) 102179 as interpreted by NSTS 18798, JSC memo TA-92-038, such that electrical faults do not damage EXPRESS Rack wiring nor present a hazard to the EXPRESS Rack, other ISS hardware items, other payloads, or crew. (6.2.3C)

4. N/A

Description of Verification Method:1. Verify by test that the payload is compatible with the SSPC current limit characteristics as

described in the IDD.

2. Verify by test or analysis that the payload is compatible with the SSPC activation characteristics as described in the IDD.

3. Verify by analysis that the payload electrical power distribution circuitry meets the design criteria of NASA TM 102179 as interpreted by NSTS 18798, JSC memo, TA-92-038, as described in the IDD.

4. N/A




L-4.5 mo





B-36

SSP 53074-PVP, Draft 16/28/02



EL-ER-006 Current Limiting T or A



1. COC



L-4.5 mo


NASA Technical Memo 102179NSTS 1700.7, ISS Addendum: par 213.1NSTS 18798: JSC memo TA-92-038SSP 52000-IDD-ERP: par 6.2.3A-C, 14.1.3 (refers to 6.2.2 and 6.2.3)

B-37

SSP 53074-PVP, Draft 16/28/02



EL-ER-007 Ripple and Transient Spikes (Repetitive) Limits - ISS T


Electrical Verification Requirement:1. Ripple limits for electrical power provided by the EXPRESS Rack SSPCM at the indicated

interfaces will not exceed the voltage values shown in the IDD figure. Payloads shall be compatible with these characteristics. (6.4)

2. Startup condition spikes for electrical power provided by the EXPRESS Rack SSPCM will not exceed the envelope shown in the IDD figure. Payloads shall be compatible with these characteristics. (6.4.1)

3. The differential mode Periodic and Random Deviation (PARD) will not exceed 1.0 volt peak-to-peak composite value for no load to full load over a measurable bandwidth from dc to 20 MHz. The payload shall be compatible with these characteristics. (6.4.2)

Description of Verification Method:1. Verify by test that the payload equipment is compatible with the ripple limits for electrical power

provided by the EXPRESS Rack SSPCM at the indicated interface and voltage values shown in the IDD figure.

2. Verify by test that the payload equipment is compatible with the EXPRESS Rack SSPCM startup condition spikes enveloped in the IDD figure.

3. Verify by test that the payload equipment is compatible with the differential mode Periodic and Random Deviation not to exceed 1.0 volt peak-to-peak composite value for no load to full load over a measurable bandwidth from dc to 20 MHz.Note: This requirement can be satisfied during CS01 and CS02 testing by increasing the lower limit from .28 Vrms to .354 Vrms. This lower limit will occur around 30 kHz for the CS01 test and remain at .354 Vrms to 50 kHz. The CS02 test limit should be set at .354 Vrms for frequencies from 50 kHz to 20 MHz. The CS02 test limit from 20 MHz to 50 MHz would remain at .28 Vrms.




L-4.5 mo


1. On-orbit subrack PL changeout: Same as the “Required Verification Data” identified above. 2. Payloads remaining on-orbit past the original period of certification of the safety features or

inhibits must perform a re-verification of the activities as identified in the “Description of the Verification Method” identified above.


B-38

SSP 53074-PVP, Draft 16/28/02



EL-ER-007 Ripple and Transient Spikes (Repetitive) Limits - ISS T



1. COC



L-4.5 mo


S683-46314SSP 30237, CS06SSP 52000-IDD-ERP: par 6.4, 6.4.1, 6.4.2Note: The Suitcase Simulator (ScS) does not provide a flight-like simulation of the EXPRESS Rack

SSPCM power output.

B-39

SSP 53074-PVP, Draft 16/28/02



EL-ER-008 Batteries A and T



Payloads shall meet the requirements for batteries, as specified in NSTS 20793 and NSTS 1700.7 Addendum. (6.5.2.1)


Verify by analysis and testing that the payload batteries meet the requirements specified in NSTS 20793 and NSTS 1700.7 Addendum.




L-4.5 mo






1. COC



L-4.5 mo


NSTS 1700.7, ISS Addendum: par 213.2NSTS 20793SSP 52000-IDD-ERP: par 6.5.2.1

B-40

SSP 53074-PVP, Draft 16/28/02



EL-ER-010 Electrical Hazards A and/or T, A or D



1. A. If the exposure condition exceeds the threshold for shock, but is below the threshold of the let-go current profile (critical hazard) as defined in IDD Table 6-II, two independent controls (e.g., a safety (green) wire, bonding, insulation, leakage current levels below maximum requirements) shall be provided such that no single failure, event, or environment can eliminate more than one control. (6.5.2.3B)

B. If the exposure condition exceeds both the threshold for shock and the threshold of the let-go current profile (catastrophic hazardous events) as defined in IDD Table 6-II, three independent controls shall be provided such that no combination of two failures, events, or environments can eliminate more than two controls. (6.5.2.3C)

C. If two dependent controls are provided, the physiological effect that a crewmember experiences as a result of the combinations of the highest internal voltage applied to or generated within the equipment and the frequency and waveform associated with a worst-case credible failure shall be below the threshold of the let-go current profile as defined in IDD Table 6-II. (6.5.2.3D)

D. If it cannot be demonstrated that the hazard meets the conditions of IDD paragraph 6.5.2.3A, B, or C, three independent hazard controls shall be provided such that no combination of two failures, events, or environments can eliminate more than two controls. (6.5.2.3E)

2. Loss of ISS or EXPRESS Rack-supplied power to the payload element during on-orbit operation will require manual reconfiguration of EXPRESS Rack power to restore power to the payload but shall not result in a hazardous condition. (6.5.3)

3. Switches/controls shall be employed that prevent automatic starting after an overload-initiated shutdown. (6.5.3.1)

4. For emergency operational modes, the payloads shall be able to sustain a safe condition with permanent loss of power. (6.5.4)

5. The payload shall provide means for its power activation/deactivation via crew control. (6.5.5)

Note: This could be done by utilizing a switch or circuit breaker which can be activated either remotely (via ground command or EXPRESS Rack laptop) or manually.

B-41

SSP 53074-PVP, Draft 16/28/02






1. For equipment other than bioinstrumentation equipment, verification of hazard controls shall be by analysis and/or test. The analysis and/or test shall: (1) define the maximum voltage and current profiles to which a crew member might be exposed by the worst case combination of credible failures, events, and/or environments the equipment might experience, and (2) show that the crew is protected by the controls incorporated in the equipment. Verification shall be considered successful when the analysis and/or test shows that the appropriate requirements from 1A, 1B, 1C, and 1D are satisfied.

A. If the exposure condition exceeds the threshold for shock, but is below the threshold of the let-go current profile (critical hazard) as defined in IDD Table 6-II, two independent controls (e.g., a safety (green) wire, bonding, insulation, leakage current levels below maximum requirements) shall be provided such that no single failure, event, or environment can eliminate more than one control.

B. If the exposure condition exceeds both the threshold for shock and the threshold of the let-go current profile (catastrophic hazardous events) as defined in IDD Table 6-II, three independent controls shall be provided such that no combination of two failures, events, or environments can eliminate more than two controls.

C. If two dependent controls are provided, the physiological effect that a crewmember experiences as a result of the combinations of the highest internal voltage applied to or generated within the equipment and the frequency and waveform associated with a worst-case credible failure shall be below the threshold of the let-go current profile as defined in IDD Table 6-II.

D. If it cannot be demonstrated that the hazard meets the conditions of IDD paragraph 6.5.2.3A, B, or C, three independent hazard controls shall be provided such that no combination of two failures, events or environments can eliminate more than two controls.

2. Verify by analysis that the loss or restoration of ISS or EXPRESS Rack-supplied power to the payload does not result in a hazardous condition.

3. Verify by analysis that the payload employs switches/controls that prevent automatic starting after an overload-initiated shutdown.

4. Verify by analysis that the payload is able to sustain a safe condition with permanent loss of power during emergency operational modes.

5. Verify by analysis or demonstration that the payload has provided means for its power activation/deactivation via crew control.

B-42

SSP 53074-PVP, Draft 16/28/02








L-4.5 mo






1. COC



L-4.5 mo


NSTS 1700.7, ISS Addendum: par 200.4ASSP 50005: par 6.4.3, 6.4.3.15SSP 52000-IDD-ERP: par 6.5.2.3B-E, 6.5.3, 6.5.3.1, 6.5.4, 6.5.5

B-43

SSP 53074-PVP, Draft 16/28/02



EL-ER-011 Electrical Connectors A and I



1. The powered side of the connector pair shall be terminated in sockets rather than pins. (6.6.1)

2. Payload connectors shall be selected and applied such that they have sufficient mechanical protection to minimize inadventent crewmember contact with exposed electrical contacts. (6.6.5)

3. Each EXPRESS Rack payload shall have a label affixed to the front panel in the area of and/or close to the power interface connector identifying the current value which the SSPCM will be set (i.e., 5A, 10A, 15A, 20A). This shall be done for each individual interface to the EXPRESS rack power system. This label shall be configured as a warning label per the requirements of Appendix E in the IDD. (6.6.6)


1. Verify by analysis of the electrical drawing/schematics that the powered side of the connector pair is terminated in sockets rather than pins.

Verify by inspection of hardware that the powered side of the connector pair is terminated in sockets rather than pins.

2. Verify by analysis that connectors have sufficient mechanical protection to minimize crewmember contact with exposed electrical contacts.

3. Verify by inspection of payload hardware that labels are affixed to the front panel in the area of and/or close to the power interface connector identifying the current value which the SSPCM will be set (i.e., 5A, 10A, 15A, 20A). Verify by inspection that this is done for each individual interface to the EXPRESS Rack power system.

Verify by inspection that that label is configured as a warning label per the requirements of Appendix E in the IDD.




L-4.5 mo




B-44

SSP 53074-PVP, Draft 16/28/02



EL-ER-011 Electrical Connectors A and I





1. COC



L-4.5 mo


NSTS 18798: memo MA2-97-093SSP 52000-IDD-ERP: par 6.6.1, 6.6.5, 6.6.6Note: The Suitcase Simulator (ScS) will be provided with cables that will interface to the flight

connectors on the payloads.

B-45

SSP 53074-PVP, Draft 16/28/02



EL-ER-012 Electrical Connectors Mating/Demating(Unpowered)

A



Payload connectors shall not be mated or demated until voltages have been removed (dead-faced) from the powered side(s) of the connectors. (6.6.2)


Verify by analysis that connectors are not mated or demated until power is removed from the powered side(s) of the connectors.




L-4.5 mo






1. COC



L-4.5 mo


SSP 50005: par 6.4.3.7SSP 52000-IDD-ERP: par 6.6.2

B-46

SSP 53074-PVP, Draft 16/28/02



EL-ER-014 Electrical Connector Mismating Prevention A and I



1. The design of electrical connectors shall make it physically incompatible to inadvertently reverse a connection or mate the wrong connectors if a hazardous condition can be created. (12.7.1)

2. N/A

3. N/A

4. N/A

5. N/A

6. N/A


1. Verify by analysis of the connectors that it is physically incompatible to inadvertently reverse a connection or mate the wrong electrical connector if a hazardous condition can be created.

2. N/A

3. N/A

4. N/A

5. N/A

6. N/A




L-4.5 mo





B-47

SSP 53074-PVP, Draft 16/28/02



EL-ER-014 Electrical Connector Mismating Prevention A and I



1. COC



L-4.5 mo


NSTS 1700.7, ISS Addendum: par 221SSP 50005: par 6.4SSP 52000-IDD-ERP: 12.7.1

Note: It is recommended the connector placement and mate/demate operations be reviewed by the JSC flight crew office prior to implementation.

B-48

SSP 53074-PVP, Draft 16/28/02



EL-ER-015 Conducted and Radiated Emissions T and A



1. Testing of equipment shall be performed using the test methods given in SSP 30238 and as amended below. (7.3.1)

2. Payload CE01 and CE03 narrowband conducted emissions in excess of the values shown in the IDD shall not appear on dc input power leads. The emissions limit shown in the IDD is for equipment drawing 1 A or less. For equipment drawing more than 1 A, the limit, in dB shown in the IDD shall be raised by 20 log I, where I equals the total dc current used by the Equipment Under Test (EUT). (7.3.1.3.2, 7.3.1.3.4)

3. The payload, designed in accordance with these EMC requirements, shall not malfunction, and performance shall not be degraded during conductive and radiated emission EMI testing. (7.3.1.1)

4. N/A

5. The payload shall use the LISN shown in the IDD for CE07 testing. (7.3.1.3.6)

6. The payload CE07 on/off and operation mode switching transients shall not exceed the envelope defined by the values listed in the IDD. (7.3.1.3.6)

7. Repetitive on/off and mode switching transients shall not occur more frequently than every 100 milliseconds. The EMI test methods for CE07 shall be as specified in SSP 30238 and as modified in 5, 6, and 7 below. (7.3.1.3.6)

8. Payload RE02 E-field emissions shall not be radiated in excess of those specified in the IDD. Above 30 MHz, the limits shall be met for both horizontally and vertically polarized waves. Measurement shall be made in the peak detector mode. (7.3.1.5.3)

The EMI test methods for RE02 shall be as specified in SSP 30238 and as modified in 8 and 9 below.

9. Payload RE02 narrowband E-field emissions shall not be radiated in excess of the values shown in the IDD at the required test distance, 1 meter. (7.3.1.5.4)


1. SSP 30238, Figure 3.2.1.1.3-1, shows the typical test setup for CE01 and CE03 testing. The EMI test methods shall be as specified in SSP 30238 and as modified in 2, 3, and 4 below.

2. Verify by test that the payload CE01 narrowband conducted emissions in excess of the values shown in the IDD do not appear on dc input power leads. Emissions that exceed the noise floor or 20 dB below the limit, whichever is greater, shall be logged and reported in the test report.

B-49

SSP 53074-PVP, Draft 16/28/02






Verify by test that the payload CE03 narrowband conducted emissions in excess of the values shown in the IDD do not appear on dc input power leads. Emissions greater than 20 dB below the specified limits shall be logged and reported in the test report. In cases where the noise floor and ambient are not 20 dB below the specified level, only those emissions above the noise floor/ambient are required to be recorded. The sensitivity of the measuring instrumentation must be such that the noise floor is at least 10 dB below the specification limit.

Measurements are taken with the interference analyzer. The measuring instrument bandwidth is less than one third the lowest tuned frequency in the range.

RECOMMENDED NARROWBAND BANDWIDTHS

Tuned Frequency (Hz) Bandwidth Range (Hz)

10 - 300 1 - 3030 - 3 K 5 - 50

3 K - 30 K 10 - 50030 K - 1 M 300 - 5 K1 M - 30 M 1 K - 50 K

30 M - 1 G 1 K - 100 K1 G - 10 G 100 K - 50 M

13.5 G - 15.5 G 1 M

3. Verify by analysis that the payload did not malfunction and payload performance was not degraded during conductive and radiated emission EMI testing.

4. N/A

5. SSP 30238, Figure 3.2.1.3.3-1, shows the typical test setup for CE07 testing. Use the LISN for CE07 testing shown in the IDD.

6. Verify by test that the payload CE07 on/off and operating mode switching transients do not exceed the envelope defined by the values listed in the IDD.

7. Verify by test that the payload repetitive on/off and mode switching transients do not occur more frequently than every 100 milliseconds.

8. Verify by test that payload RE02 E-field emissions are not radiated in excess of those specified in the IDD. Above 30 MHz, the limits shall be met for both horizontally and vertically polarized waves. Measurement shall be made in the peak detector mode. See 2 above for measuring instrument bandwidth.

B-50

SSP 53074-PVP, Draft 16/28/02





Description of Verification Method: (Continued)1. Verify by test that the payload RE02 narrowband E-field emissions are not radiated in excess of

the values shown in the IDD at the required test distance, 1 meter.

Note: The payload EMI/EMC test procedure is required to be submitted to the EMI/EMC test facility 30 days in advance of the test date.


Analysis report and signed test report.


L-9.5 mo








L-4.5 mo


NSTS 1700.7, ISS Addendum: par 212.2SSP 30238SSP 52000-IDD-ERP: par 7.3.1, 7.3.1.1, 7.3.1.3.2, 7.3.1.3.4, 7.3.1.3.6, 7.3.1.5.3, 7.3.1.5.4

B-51

SSP 53074-PVP, Draft 16/28/02



EL-ER-016 Conducted and Radiated Susceptibility T and A



1. Compliance with the susceptibility limits is not required. The susceptibility test data shall be evaluated against the limits in the IDD. The threshold of susceptibility shall be determined for equipment unable to meet the susceptibility test limits. This value shall be recorded. (7.3.1)

2. The payload shall not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when subjected to electromagnetic energy injected onto its power leads less than or equal to the CS01 values as shown in the IDD. (7.3.1.1)

The CS01 requirement is also considered met when the audio power source specified in SSP 30238 adjusted to dissipate 50 W in a 0.5-ohm load, cannot develop the required voltage at the EUT power input terminals, and the EUT is not susceptible to the output of the signal source. (7.3.1.4.2)

SSP 30238, Figure 3.2.2.1.3-1, shows the typical test setup for CS01 testing. The EMI test methods shall be as specified in SSP 30238 and as modified in 1 and 2 below.

3. Payloads shall not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when subjected to 0.28 Vrms from a 50-ohm source. The test signal shall be applied to the equipment power line near the equipment input terminals. (7.3.1.4.4)

The CS02 requirement is also considered met under the following condition: when a 1-W source of 50 ohms impedance cannot develop the required voltage at the EUT power input terminals, and the EUT is not susceptible to the output of the signal source.

SSP 30238, Figure 3.2.2.2.3-1, shows the typical test setup for CS02 testing. The EMI test methods shall be as specified in SSP 30238 and as modified in 1 and 3 below.

4. Payloads shall not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when the CS06 test spikes, each having the waveform shown in the IDD figure, are applied sequentially to the dc power input leads. The values of E and t are as given in the IDD. Each spike shall be superimposed on the power line voltage waveform. (7.3.1.4.6)

SSP 30238, Figure 3.2.2.2.4-1 or 3.2.2.2.4-2, shows the typical test setup for CS06 testing. The EMI test methods shall be as specified in SSP 30238 and as modified in 1 and 4 below.

5. Payloads shall not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when subjected sequentially to the RS02 test spikes, each having the waveform shown in the IDD (Figure 7-4), with the values of E and t which that are given in the IDD. (7.3.1.6.3)

B-52

SSP 53074-PVP, Draft 16/28/02





Electrical Verification Requirement: (Continued)

The EMI test methods for RS02 shall be as specified in SSP 30238 and as modified in 1 and 5 below.

6. Payloads shall not produce an unsafe condition or one that could result in damage to ISS equip-ment or payload hardware when subjected to the RS03 radiated electric fields less than or equal to those specified in the IDD. Above 30 MHz, the requirement shall be met for both horizontally and vertically polarized waves. As a minimum, the levels in the IDD apply at either the specific frequencies stated or across the ranges stated. (7.3.1.7.2)

The EMI test methods for RS03 shall be as specified in SSP 30238 and as modified in 1 and 6 below.

7. N/A

Description of Verification Method:1. When an EUT susceptibility is noted, the output level shall be decreased to determine the

susceptibility threshold level. This value shall be recorded. The susceptibility threshold level is defined as the point when payload science is affected.

2. Verify by test and analysis that the payload does not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when subjected to electromagnetic energy injected onto its power leads less than or equal to the values as shown in the IDD.The CS01 requirement is also met when the audio power source, adjusted to dissipate 50 W in a 0.5-ohm load, cannot develop the required voltage at the EUT power input terminals, and the EUT is not susceptible to the output of the signal source.

3. Verify by test and analysis that the payload does not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when subjected to electromagnetic energy injected onto its power leads less than or equal to the values as shown in the IDD.The LISN is a 20 H inductor in the lead being tested.The CS02 requirement is also considered met under the following condition: when a 1-W source of 50 ohms impedance cannot develop the required voltage at the EUT power input terminals, and the EUT is not susceptible to the output of the signal source.

4. Verify by test and analysis that the payload does not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when the CS06 test spikes, each having the waveform shown in the IDD figure, are applied sequentially to the dc power input leads. The values of E and t are as given in the IDD. Each spike shall be superimposed on the power line voltage waveform.

B-53

SSP 53074-PVP, Draft 16/28/02






5. Verify by test and analysis that the payload does not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when the payload is subjected sequentially to the RS02 test spikes. Each spike will have the waveform shown in the IDD (Figure 7-4), as well as the values of E and t which are given in the IDD.

6. Verify by test and analysis that the payload does not produce an unsafe condition or one that could result in damage to ISS equipment or payload hardware when subjected to the RS03 radiated electric fields less than or equal to those specified in the IDD. Above 30 MHz, the requirement shall be met for both horizontally and vertically polarized waves. As a minimum, the levels in the IDD apply at either the specific frequencies stated or across the ranges stated.

Note: The payload EMI/EMC test procedure is required to be submitted to the EMI/EMC test facility 30 days in advance of the test date.

7. N/A


Analysis report and signed test report.


L-9.5 mo








L-4.5 mo


NSTS 21000-IDD-ISS: par 10.7.2.2.1.2SSP 30238SSP 52000-IDD-ERP: par 7.3.1, 7.3.1.1, 7.3.1.4.2, 7.3.1.4.4, 7.3.1.4.6, 7.3.1.6.3A-B, 7.3.1.7.2

B-54

SSP 53074-PVP, Draft 16/28/02



EL-ER-017 ESD Compatibility/Labeling A and I


Electrical Verification Requirement:1. Unpowered Payload Developer electrical equipment and components shall either fail safe or shall

not be damaged by Electrostatic Discharge (ESD) equal to or less than 4,000 V to the case or any pin on external connectors or incorporate adequate protection measures into the hardware design to ensure the unpowered PD electrical equipment is not damaged during ground and on-orbit installation activities. Protection measure will include, at a minimum, protective caps/covers, handling procedures and ESD sensitive identification labels. (7.3.2.1)

2. N/A

Description of Verification Method:1. Verify by analysis that the payload unpowered PD electrical equipment and components meet the

ESD requirements (either fail safe or not be damaged by Electrostatic Discharge (ESD) equal to or less than 4,000 V to the case or any pin-on external connectors) in the IDD, or an inspection of the as-built flight hardware must be performed to verify proper inclusions of the protection measures including protective caps/covers, handling procedures and ESD sensitive identification labels.

2. N/A




L-4.5 mo


1. On-orbit subrack PL changeout: Same as the “Required Verification Data” identified above.2. Payloads remaining on-orbit past the original period of certification of the safety features or




1. COC



L-4.5 mo

Applicable Documents and Notes:MIL-STD-1686SSP 52000-IDD-ERP: par 7.3.2.1, 12.5, Appendix E, Section 3.5.9I

B-55

SSP 53074-PVP, Draft 16/28/02



EL-ER-018 Corona T, A or T



Electrical and electronic subsystems, equipment, and systems shall be designed to preclude damaging or destructive corona in its operating environment. (7.3.2.3)


Payloads with operating voltages greater than 190 volts or payloads containing gaseous mixtures other than those present in the pressurized module shall be verified by analysis or test to the degree necessary to ensure no permanent damaging effects and no hazardous conditions due to destructive corona will exist in its operating environment. If the equipment (with voltages greater than 190 volts) may be powered during depressurization, the verification shall be by test.


Analysis Report and/or Test Report.


L-9.5 mo

Description of Reverification Requirements:1. On-orbit subrack PL changeout: Same as the “Required Verification Data” identified above.2. Payloads remaining on-orbit past the original period of certification of the safety features or



Required Reverification Data:1. COC2. Same as “Required Verification Data” identified above.


L-4.5 mo

Applicable Documents and Notes:MSFC-STD-531SSP 52000-IDD-ERP: par 7.3.2.3

B-56

SSP 53074-PVP, Draft 16/28/02



EL-ER-019 Alternating Current (ac)/Direct Current (dc) Magnetic Fields for EXPRESS Rack Payloads in the ISS

T and T or A



1. The generated ac magnetic fields, measured at a distance of 2.76 in (7 cm) from any equipment, shall not exceed 140 dB above 1 pT for a frequency at 30 Hz, then falling 26.5 dB per decade to 3.5 kHz, and 85 dB per decade to 3.5 kHz, and 85 dB per decade for frequencies ranging from 3.5 kHz to 50 kHz. Tests shall be performed using the MIL-STD-462D RE101 method as modified below. (7.4.3.1)

2. The generated dc magnetic fields shall not exceed 170 dBpT at a distance of 2.76 in (7 cm) from any equipment. This requirement applies to intentional electromagnetic and permanent devices. (7.4.3.2)


1. Verify by test or analysis that the generated ac magnetic fields, measured at a distance of 2.76 in (7 cm) from any equipment, do not exceed 140 dB above 1 pT for a frequency at 30 Hz, then falling 26.5 per decade to 3.5 kHz, and 85 dB per decade for frequencies ranging from 3.5 kHz to 50 kHz. Tests will be performed using the MIL-STD-462D RE101 method with the following modifications:

A. Test Setup guidelines are per SSP 30238, Figures 3.2.3.1.4-1 or 3.2.3.1.4-2, not the setup identified by MIL-STD-462D.

B. Guidelines of SSP 30238, Figures 3.2.3.1.4-1 and 3.2.3.1.4-2, requirement of 1 meter separation does not apply to RE101.

C. Measurements are required from 30 Hz to 50 kHz rather than 100 kHz required by MIL-STD-461D.

D. Measurements are performed at 7 cm from the generating equipment. In the event emissions are out-of-specification, measurements are performed at 50 cm from the generating equipment.

E. Emissions greater than 20 dB below the specified limits will be recorded in the EMI test report. In cases where the noise floor and ambient are not 20 dB below specified level, only those emissions above the noise floor/ambient are required to be recorded.

F. Alternate automated scanning methods are acceptable.

i. Spatial scanning of the probe with receiver in max hold mode. Receiver is continuously scanning in frequency and the loop sensor is manually scanning over the faces of the box while being careful not to let the probe scan out-run the frequency scan of the receiver.

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SSP 53074-PVP, Draft 16/28/02



EL-ER-019 Alternating Current (ac)/Direct Current (dc) Magnetic Fields for EXPRESS Rack Payloads in the ISS

T and T or A



ii. Frequency scans in multiple positions. This method involves doing a frequency scan with the probe in a fixed orientation and location. The orientation and position of the probe is then varied to obtain multiple plots of the magnetic field.

2. Verify by test or analysis that the generated dc magnetic fields do not exceed 170 dBpT at a distance of 2.76 inches (7 cm) from any equipment. For payload equipment that exceeds the design requirements, measurements or analysis at 10-cm from the generating equipment will be performed. Additional measurements or analysis will be performed at 10-cm increments away from the generating equipment until data proves the dc magnetic fields are 6 dB below the 170 dB above 1 pT requirement.

This requirement applies to intentional electromagnetic and permanent magnet devices.


Signed test report.


L-9.5 mo








L-4.5 mo


SSP 30238SSP 52000-IDD-ERP: par 7.4.3.1, 7.4.3.2

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SSP 53074-PVP, Draft 16/28/02



EL-ER-020 Electrical Bonding A and/or T



The payload-to-EXPRESS Rack electrical bonding interface shall be electrically bonded to provide homogeneous electrical characteristics. All electrical and mechanical elements shall be securely bonded to structure in accordance with SSP 30245. Four classes of bonds are applicable to either middeck, EXPRESS Rack, or both: Classes C, H, R, and S. These bond classes are defined in the following paragraphs. These definitions will be used in further discussion on bonding requirements. (7.5.1)

A. Fault Current Bond - Class C

All payload elements using EXPRESS Rack facility power shall have mechanically secure electrical connections to the EXPRESS Rack structure capable of carrying the maximum return fault current [see paragraph 6.2.3 (Current Limiting)]. (7.5.1A)

B. Shock Hazard - Class H

Exposed conducting frames or parts of electrical or electronic equipment shall have a low resistance bond of less than 0.1 ohm to conducting structure. If the equipment design includes a ground terminal or pin which is internally connected to exposed parts, a ground connection to the terminal or pin shall be provided. (7.5.1B)

C. RF Bond - Class R

Payload elements containing electrical circuits which generate radio frequencies or circuits which are susceptible to radio frequency interference may require a low impedance path to structure in order to comply with EMC requirements. The dc resistance of the Class R bond between the EXPRESS Rack interface and structure shall be less than 2.5 milliohms for each joint. (7.5.1C)

D. Static Bond - Class S

All conducting items subject to triboelectric (frictional) or any other charging mechanism shall have a mechanically secure electrical connection to the payload element structure. The resistance of this connection shall be less than 1 ohm for each joint. (7.5.1D)


Verify by analysis that the payload-to-EXPRESS Rack electrical bonding interface is electrically bonded to provide homogeneous electrical characteristics.

Verify by analysis that all electrical and mechanical elements are securely bonded to structure in accordance with SSP 30245.

1. Verify by analysis that all payload elements using EXPRESS Rack facility power have mechanically secure electrical connections to the EXPRESS Rack structure capable of carrying the maximum return fault current.

B-59

SSP 53074-PVP, Draft 16/28/02



EL-ER-020 Electrical Bonding A and/or T



2. Verify by test or analysis that payloads exposed conducting frames or parts of electrical or electronic equipment have a low resistance bond of less that 0.1 ohm to conducting structure.

3. Verify by test or analysis that payloads requiring a Radio Frequency (RF) bond (Class R) have a dc resistance between the payload and the EXPRESS Rack interface less than 2.5 milliohms for each joint.

4. Verify by test or analysis that payload conducting items subject to triboelectric (frictional) or any other charging mechanism have a mechanically secure electrical connection to the payload element structure. Resistance of this connection is less than 1 ohm for each joint.




L-4.5 mo






1. COC



L-4.5 mo


SSP 30245SSP 52000-IDD-ERP: par 7.5.1, 7.5.1A-D

B-60

SSP 53074-PVP, Draft 16/28/02



EL-ER-021 Electrical Bonding of Payload Hardware T and A



1. Equipment which generates and/or is susceptible to RF interference shall have a Class R bond. In addition, the metallic shells of all external electrical connectors shall be electrically bonded to the equipment case or the payload equipment bulkhead mount with a dc resistance of less than 2.5 milliohms per joint. (7.5.1.1)

2. Wire harness shields external to equipment, requiring grounding at the payload equipment, shall have provisions for grounding the shields to the payload equipment through the harness connector backshell or for carrying single point grounded shields through the connector pins. (7.5.1.1)


1. On equipment which generates and/or is susceptible to RF interference, verify by test that the metallic shell of all external electrical connectors are electrically bonded to the payload equipment case or the payload equipment bulkhead mount with a dc resistance of less than 2.5 milliohms per joint.

2. Verify by analysis that wire harness shields external to equipment, requiring grounding at the payload equipment, have provisions for grounding the shields to the payload equipment through the harness connector backshell or for carrying single point grounded shields through the connector pins.




L-4.5 mo





B-61

SSP 53074-PVP, Draft 16/28/02



EL-ER-021 Electrical Bonding of Payload Hardware T and A



1. COC



L-4.5 mo


SSP 30245SSP 52000-IDD-ERP: par 7.5.1.1

B-62

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EL-ER-022 Electrical Bonding of Payload Structures A and T and I



1. The primary payload bond path is through the EXPRESS Rack-to-payload power connector interface. The bond path shall be accomplished by a single 12-AWG wire in the primary power connector capable of carrying a current of 24 A.

EXPRESS Rack payload bonds shall meet the appropriate bond class requirements of paragraph 7.5.1, “Electrical Bonding,” and EXPRESS Rack payloads shall have less than or equal to 2.5 milliohms at each junction of the fault bond interface. The dc resistance from the payload’s power connector ground pin (pin D for MDLs or pin 12 for ISIS drawers) to the payload’s external conductive chassis shall not exceed 50 milliohms. (7.5.1.2.1.1)

2. N/A

3. The payload-to-EXPRESS Rack mated surface bond (defined as the payload, adapter plate, or MDL surface that attaches to the EXPRESS Rack backplate) is a removable bond and shall be nickel or nickel plated per SSP 30245 using methods in MIL-C-26074 or D683-29033-1. The maximum resistance between the mated surfaces of the bond connection (connector to mounting base, mounting base to EXPRESS Rack, or when applicable, mounting base to payload) shall be less than or equal to 2.5 milliohms (Class R) at each junction of the fault current bond interface. (7.5.1.2.1.3)

All the aluminum surfaces used for permanent bonding in the payload shall be originally cleaned to bare metal, then chemically filmed per MIL-C-5541, Class 3 (gold alodine 1200LN9368 or equivalent) or nickel plated using methods in MIL-C-26074.


1. Verify by Test that the dc resistance from the payload’s power connector ground pin (pin D for MDLs or pin 12 for ISIS drawers) to the payload’s external conductive chassis does not exceed 50 milliohms.

2. N/A

3. Verify by analysis that the payload-to-EXPRESS Rack mated surface bond (defined as the payload, adapter plate, or MDL surface that attaches to the EXPRESS Rack backplate) is nickel or nickel-plated per SSP 30245 using methods in MIL-C-26074.

Verify by analysis that all aluminum surfaces used for permanent bonding in the payload are originally cleaned to bare metal, then chemically filmed per MIL-C-5541, Class 3 (gold alodine 1200LN9368 or equivalent) or nickel-plated using methods in MIL-C-26074.

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EL-ER-022 Electrical Bonding of Payload Structures A and T and I


Description of Verification Method: (Continued)Verify by test that the maximum resistance between the mated surfaces of the bond connection (connector to mounting base, mounting base to EXPRESS Rack, or when applicable, mounting base to payload) is less than or equal to 2.5 milliohms at each junction of the fault current bond interface.




L-4.5 mo






1. COC



L-4.5 mo


D683-29033-1MIL-C-5541MIL-C-26074 MIL-STD-1686SSP 30245SSP 52000-IDD-ERP: par 7.5.1.2.1.1, 7.5.1.2.1.3

B-64

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EL-ER-023 Power Circuit Isolation and Grounding T and A



1. Payload input power and return lines shall be isolated from structure by at least 1.0 megohm with a parallel capacitance of 10 µF measured at the payload interface connector contacts. Isolation and grounding requirement for the payload power and signal interfaces shall be per the IDD figure. (7.6.1)

2. EXPRESS Rack 28-Vdc primary power bus and payload secondary power shall be isolated by a minimum of 1.0 megohm. Secondary power return lines shall be connected to chassis at no more than one point when termination to chassis is desired. If payload secondary power is distributed to equipment outside the box, the return line is to be grounded to chassis at the source. (7.6.3)


1. Verify by test that the payload input power and return lines are isolated from structure by at least 1.0 megohm with a parallel capacitance of 10 µF measured at the payload interface connector contacts. Test with equipment in operating configuration (power control switch closed) but no power applied.

Verify by analysis that the isolation and grounding requirements for the payload power and signal interfaces are per the IDD figure.

2. Verify by test that the EXPRESS Rack 28-Vdc primary power bus and payload secondary power are isolated by a minimum of 1.0 megohm. Test with equipment in operating configuration (power control switch closed) but no power applied.

Verify by test or analysis that secondary power return lines are connected to chassis at no more than one point when termination to chassis is desired.Verify by test and analysis that secondary power that is distributed to equipment outside the box is single point grounded at the source.




L-4.5 mo




B-65

SSP 53074-PVP, Draft 16/28/02



EL-ER-023 Power Circuit Isolation and Grounding T and A





1. COC



L-4.5 mo


NSTS 1700.7BSSP 30240SSP 52000-IDD-ERP: par 7.6.1, 7.6.3

B-66

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EL-ER-024 Signal Isolation and Grounding Requirements A, A and T



1. Isolation and grounding for ethernet received and transmitted signals shall be per IEEE 802.3. (7.7.1)

2. N/A

3. N/A

4. N/A

5. Payload video transmitting signal return lines shall be referenced to signal ground. (7.7.5)

6. The design criteria for wire shield references shall be per the data given in the IDD table. (7.7.6)


1. Verify by analysis that isolation and grounding for ethernet received and transmitted signals are per IEEE 802.3.

2. N/A

3. N/A

4. N/A

5. Verify by analysis that video transmitting signal return lines are referenced to signal ground.

Note: Video signal transmitters should not be referenced to power ground. Signal transmitters that are single ended should have their signal return line tied to signal ground at the source. Signal transmitters that are complementary or balanced should be referenced to signal ground through the transmitting device.

6. Verify by analysis that the design criteria for wire shield references is per the data given in the IDD table.




L-4.5 mo




B-67

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EL-ER-024 Signal Isolation and Grounding Requirements A, A and T





1. COC



L-4.5 mo


ANSI/EIA RS-422BIEEE 802.3SSP 30240SSP 52000-IDD-ERP: par 7.7.1, 7.7.5, 7.7.6

B-68

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EL-ER-026 Pin Functions MDLs/MDL Replacement/ISIS Drawers

A



1. Connector pin functions for MDL or MDL replacement payloads shall be as shown in Table 8-I. (8.1.1.1)

2. N/A

3. N/A


1.Verify by analysis that the payload connector pin functions for MDL or MDL replacement payloads are as shown in Table 8-I of the IDD.

2.N/A

3.N/A




L-4.5 mo






1. COC



L-4.5 mo



B-69

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EL-MD-001 In-Flight dc Power Bus Ripple/Transient Spikes(Repetitive) at the Interface - Shuttle

T


Electrical Middeck Verification Requirement:

1. Payload equipment shall be compatible with the in-flight dc power bus ripple at the Shuttle interface: 0.90 V peak-to-peak narrowband (30 Hz to 7 kHz) falling 10 dB per decade to 0.28 V peak-to-peak at 70 kHz, thereafter remaining constant to 400 MHz. (6.3.1A, 7.2.1)

Payload equipment shall be compatible with the on-orbit, during the Orbiter hydraulic circulation pump startup conditions (<300 ms), sawtooth ripple voltage of 4 V peak-to-peak amplitude that appear on the 28 Vdc power bus at a frequency of 500 to 700 Hz.

Payload equipment shall be compatible with the in-flight dc power bus ripple at the interface: The momentary coincidence of two or more signals at any one frequency will not exceed the envelope defined as 1.6 V peak-to-peak (30 Hz to 7 kHz), falling 10 dB per decade to 0.5 V peak-to-peak at 70 kHz, thereafter remaining constant to 400 MHz. (6.3.1B, 7.2.1)

2. The payload equipment shall be compatible with the in-flight dc power transient spikes (measured differential mode) not to exceed twice the line voltage relative to the line voltage for either positive or negative transients. (6.3.2, 7.2.1)


1. Verify by test that the payload equipment is compatible with the in-flight dc power bus ripple at the interface as described in NSTS 21000-IDD-MDK.

2. Verify by test that the payload equipment is compatible with the in-flight dc power transient spikes (measured differential mode) not to exceed twice the line voltage relative to the line voltage for either positive or negative transients.




L-4.5 mo





B-70

SSP 53074-PVP, Draft 16/28/02



EL-MD-001 In-Flight dc Power Bus Ripple/Transient Spikes(Repetitive) at the Interface - Shuttle

T



1. COC



L-4.5 mo


NSTS 21000-IDD-MDK: par 7.2.2SSP 52000-IDD-ERP: par 6.3.1A-B, 6.3.2, 7.2.1

B-71

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EL-MD-002 Ground dc Power - Shuttle/Middeck T



If powered on the ground in the Shuttle (i.e., prelaunch and/or postlanding), the payload shall be compatible with the following ground dc power specifications: (6.3.3)

1. The narrowband ripple voltage at the interface will not exceed an envelope with limits of 1.2 V peak-to-peak (30 Hz to 7 kHz), falling log-linear to 0.28 V peak-to-peak at 70 kHz, thereafter remaining constant to 400 MHz. (6.3.3A)

2. The momentary coincidence of two or more signals at any one frequency will not exceed an envelope with limits of 2 V peak-to-peak (30 Hz to 7 kHz), falling log-linear to 0.5 V peak-to-peak at 70 kHz, thereafter remaining constant to 400 MHz. (6.3.3B)

3. Transient spikes (measured common mode) will not exceed the impulse equivalent of 300 x 10-6 volt seconds above or below normal line voltage. Peak transient spikes will be limited to ±50 V from nominal bus voltage on the positive line, and ±30 V from nominal on the negative line. Rise and fall time will not be less than 1 µs. (6.3.3C)

Description of Verification Method:Verify by test that the payload is compatible with the Shuttle/middeck ground dc power specifications as described in NSTS 21000-IDD-MDK.




L-4.5 mo


On-orbit subrack PL changeout: None


N/A


N/A


NSTS 21000-IDD-MDK: par 7.2.2CSSP 52000-IDD-ERP: par 6.3.3A-C

B-72

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EL-MD-004 Radiated Interference - Shuttle/Middeck T and A



1. The Shuttle-produced radiated fields environment on which payload design shall be based is limited as follows: (7.2.2, 7.3)

A. Electric fields are defined in the IDD for unintentional emissions, and for intentional emissions. The generated ac magnetic fields will be limited to less than 140 dB above 1 pT (30 Hz to 2 kHz), falling 40 dB per decade to 50 kHz. (Applies to payloads that may operate radio frequency receiving equipment or electric field sensing equipment).

B. The lightning-produced magnetic fields in the crew compartment for vehicles in flight will be limited to a peak level of 3 A/m; for vehicles on the ground protected by facility or other structures, the peak level shall be limited to 5 A/m; and for vehicles on the ground not protected by facility or other structures, the peak level will be limited to 10 A/m. The rise to peak value is 2 s, and the fall to zero value is 100 s. The payload shall be designed so that a failure due a lightning strike shall not propagate to the Shuttle.

2. EXPRESS Rack payloads when exposed to the WCCS operational frequencies and radiated field intensity, as stated in the IDD, shall not result in a hazardous condition. (7.2.1.1, 7.3)


1. Verify by test that the payload design is compatible with the Shuttle-produced radiated fields environment as follows:

Verify by test that the payload is compatible with the electric fields for unintentional emissions, and intentional emissions as defined in NSTS 21000-IDD-MDK.

Verify by test that payload design is compatible with the generated ac magnetic fields limited to less than 140 dB above 1 pT (30 Hz to 2 kHz), falling 40 dB per decade to 50 kHz.

Verify by analysis that the payload is designed so that failure of the payload due to a lightning strike will not propagate to the EXPRESS Rack facility, ISS, Shuttle, or other payloads.

2. Verify by analysis that the payload when exposed to the WCCS operational frequencies and radiated field intensity, as stated in NSTS 21000-IDD-MDK, does not result in a hazardous condition.


Signed Test Report.


L-6.5 mo



B-73

SSP 53074-PVP, Draft 16/28/02



EL-MD-004 Radiated Interference - Shuttle/Middeck T and A






1. Certificate of Compliance (COC) with the requirement



L-8.5 mo

L-6.5 mo


NSTS 1700.7B, ISS Addendum: par 212.2NSTS 21000-IDD-MDK: par 8.2.2SSP 30237SSP 30238SSP 52000-IDD-ERP: par 7.2.1.1, 7.2.2, 7.2.2B, 7.3

B-74

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EL-MD-005 Payload-Produced Conducted Noise - Shuttle T



The payload-generated conducted emission limits, applicable to all dc power interfaces, are as follows:

1. The power line conducted emissions in the frequency domain shall be limited to levels indicated in the IDD (Figure 7-5), and the steady-state ripple voltage in the time domain shall not exceed 28.45 V or drop below 27.55 V, starting at approximately 1 sec after the transient. (7.3, 7.4.1A)

2. The cargo-generated transients produced on dc power lines by switching or other operations shall not exceed the limits defined in the IDD figure when fed from a source impedance close to but not less than the values defined in Figures 8.3.1-4 and 8.3.1-5 of NSTS 21000-IDD-MDK. (The use of a battery cart is preferable to regulated dc power supplies). Each non-overlapping transient is considered independent of prior or post-transient. (7.3, 7.4.1B)

3. Rise and fall times for (B) above shall be greater than 1.0 µs. (7.3, 7.4.1C)


Verify by test that the power line conducted emissions in the frequency domain are limited to levels indicated in the IDD (Figure 7-5), and the steady-state ripple voltage in the time domain does not exceed 28.45 V or drop below 27.55 V, starting at approximately 1 sec after the transient.

Note: The test frequency range is 30 Hz to 50 MHz.

Verify by test that the payload-generated transient spikes produced on the dc power lines by switching or operations do not exceed the limits defined in the IDD figure when fed from a source impedance close to but not less than the values defined in Figures 8.3.1-4 and 8.3.1-5 of NSTS 21000-IDD-MDK. (The use of a battery cart is preferable to regulated dc power supplies.) Each non-overlapping transient is considered independent of prior or post-transients. Rise and fall times are to be greater than 1.0 µs.


Signed test report.


L-6.5 mo




B-75

SSP 53074-PVP, Draft 16/28/02



EL-MD-005 Payload-Produced Conducted Noise - Shuttle T





1. COC



L-4.5 mo


NSTS 1700.7, ISS Addendum: par 212.2NSTS 21000-IDD-MDK: par 8.3.1SSP 52000-IDD-ERP: par 7.3, 7.4.1A-C

B-76

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EL-MD-006 Payload-Produced Radiated Fields - Shuttle T and A



1. The unintentional radiated electric fields shall not exceed the levels defined in the IDD figures. (7.3, 7.4.2A)

2. The generated dc magnetic fields shall not exceed 170 dBpT at a distance of 1.0 m from any payload equipment. This limit applies to electromagnetic and permanent magnetic devices. The generated ac magnetic fields (applies at a distance of 1 m from any payload equipment) shall not exceed 130 dB above 1 pT (30 Hz to 2 kHz) falling 40 dB per decade to 50 kHz. (7.3, 7.4.2B)

3. Electrostatic discharges shall not occur within the EXPRESS Rack payload other than those isolated from the gaseous environment (hydrogen-oxygen mixture) and shielded by the payload to satisfy the requirements of subparagraph “A” above. (7.3, 7.4.2C)

4. Allowable levels of radiation from EXPRESS Rack payload or experiment transmitter systems shall be limited as shown in the IDD figure. These limits apply 1 m from window-mounted antennas. (7.3, 7.4.2D)


Verify by test that the payload unintentional radiated electric fields do not exceed the levels defined in NSTS 21000-IDD-MDK, Figures 8.3.2-1, -2, and -3 also in SSP 52000-IDD-ERP, Figures 7-7, 7-8, and 7-9.

Verify by test that the payload-generated dc magnetic fields do not exceed 170 dBpT at a distance of 1.0 m from any payload equipment. This limit applies to electromagnetic and permanent magnetic devices.

Verify by test that the payload-generated ac magnetic fields (applies at a distance of 1 m from any payload equipment) do not exceed 130 dB above 1 pT (30 Hz to 2 kHz) falling 40 dB per decade to 50 kHz.

Verify by analysis that payload electrostatic discharges do not occur within the EXPRESS Rack other than those isolated from the gaseous environment (hydrogen-oxygen mixture) and shielded by the payload design to satisfy the requirements of subparagraph “A” above.Verify by test that the EXPRESS Rack payload or experiment transmitter systems are limited as shown in NSTS 21000-IDD-MDK, Figures 8.3.2-1, -2, and -3 also in SSP 52000-IDD-ERP, Figures 7-7, 7-8, and 7-9. These limits apply 1 m from window-mounted antennas.


Signed test report.


L-6.5 mo

B-77

SSP 53074-PVP, Draft 16/28/02



EL-MD-006 Payload-Produced Radiated Fields - Shuttle T and A







1. COC



L-4.5 mo


NSTS 1700.7, ISS Addendum: par 212.2NSTS 21000-IDD-MDK: par 8.3.2SSP 52000-IDD-ERP: par 7.3, 7.4.2A-D

B-78

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CD-ER-002 RS-422, Ethernet, Analog, Discrete, Video, andPoint-to-Point Connector/Pin Interface

A and I


Command and Data Handling Verification Requirement:

Ethernet and video for MDL or MDL replacement payloads shall be as shown in Table 9-I of the IDD. (9.2.6.1, 9.7.3)


Verify by analysis that the final design cable and wire drawings reflect the connectors and pin assignments stipulated in the IDD.Verify by inspection that the flight hardware is assembled according to the final design cable and wire drawings.




L-4.5 mo


1. Same as “Verification Requirement” above.




1. Certificate of Compliance (COC) with the requirement.



L-4.5 mo


SSP 52000-IDD-ERP: par 9.2.6.1, 9.7.3Note: The Suitcase Simulator (ScS) will be provided with flight-qualified cables that will interface to

the flight connectors on the EXPRESS Rack payload.

B-79

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CD-ER-003 Ethernet Signal Interface T


Command and Data Handling Verification Requirement:1. Payloads interfacing with the EXPRESS Rack Payload Ethernet Hub Bridge (PEHB) shall meet

the requirements and signal characteristics of IEEE 802.3 (10BASE-T section). (9.2.1)2. Payloads communicating with the RIC, LAPTOP, or other EXPRESS Rack payloads via ethernet

shall use software protocol Transmission Control Protocol/Internet Protocol (TCP/IP). (9.2.2)3. All telemetry from the payload to the RIC shall be packetized.

A. Telemetry packet format shall be as shown in Table 11-VII of the IDD.B. Payload request/command format via the ethernet to/from the RIC shall be as shown in IDD

paragraphs 11.2.3.5 and Tables 11-VIII through 11-XXI and Figure 11-6 of the IDD. (9.2.3, 9.2.4, 11.2.3.5, 11.2.3.5.1, 11.2.3.5.2, 11.2.3.5.3, 11.2.3.5.4, 11.2.3.5.5.1, 11.2.3.5.5.2, 11.2.3.7)

4. Payload shall receive, process and verifying the command size as described on message byte count in the EXPRESS header. (9.2.5)

Description of Verification Method:1. Verify by test that the Payload Ethernet PEHB interface meets all the signal characteristics

requirements of IEEE 802.3 (10BASE-T section). Use of vendor test data is acceptable.2. Using GSE, verify by test that the payload ethernet software is compatible with TCP/IP protocol

as described in the IDD.3. Using Suitcase Simulator (preferred) or payload GSE, verify by test that the payload ethernet

packet telemetry format meets the requirement as described in the IDD. Verify that the payload can receive and process correct command format from the RIC up to 49 16 bit words as specified in the message byte count per 100 milliseconds.

4. Using ScS (preferred) or payload GSE, verify by test that the payload can generate and transmit the correct request format to RIC via PEHB ethernet interface as described in the IDD.

Required Verification Data:Certificate of Compliance (COC) with the requirement.

Data Submittal Dates:L-4.5 mo

Description of Reverification Requirements:1. Same as “Verification Requirement” above.2. Payloads remaining on-orbit past the original period of certification of the safety features or



B-80

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CD-ER-003 Ethernet Signal Interface T






L-4.5 mo


IEE 802.3 (10 BASE-T section)SSP 52000-IDD-ERP: par 9.2.1, 9.2.2, 9.2.3, 9.2.4, 9.2.5, 11.2.3.5, 11.2.3.5.1, 11.2.3.5.2, 11.2.3.5.3, 11.2.3.5.4, 11.2.3.5.5.1, 11.2.3.5.5.2, 11.2.3.7SSP 52000-PAH-ERP: par 4.4.2

B-81

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CD-ER-007 Video Signal Interface A and T


Command and Data Handling Verification Requirement:

Payload shall provide an Analog balanced differential video output signal, when differentially terminated in 75 5 ohms, the differential signal shall have the same color encoding, timing, and relative signal levels as defined by ANSI/SMPTE 170M. The balanced differential signal shall be derived from the single – ended signal as specified in the following: (9.7)

1. The balanced differential signal output shall be designed with a 75 5 ohms source impedance, the signal input to the EXPRESS Rack shall be differentially terminated in 75-5 ohms with the EXPRESS Rack. (9.7.1.1)

2. The positive pin of the balanced differential output shall provide a nominal 0.5 volt peak to peak signal, in phase quadrature to the positive output, with sync tip at 0 V and peak white at negative 0.5 V. (9.7.1.2)

3. The negative pin of the balanced differential output shall provide a nominal 0.5 volt peak to peak signal, in phase quadrature to the positive output, with sync tip at 0 V and peak white at negative 0.5 V. (9.7.1.3)

4. The balanced differential output shall have no more than a 0.1 Vdc common mode component measured with respect to the input ground reference pin. (9.7.1.4)


Using test data, verify by analysis that the payload balanced differential video signal meets the requirement as described in the IDD.

Using payload GSE, verify by test that the payload balanced differential video interface is functionally compliant as described in the IDD.




L-4.5 mo





B-82

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CD-ER-007 Video Signal Interface A and T










L-4.5 mo


ANSI/SMPTE 170MSSP 52000-IDD-ERP: par 9.7, 9.7.1.1, 9.7.1.2, 9.7.1.3, 9.7.1.4SSP 52000-PAH-ERP: par 4.6

B-83

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SW-ER-004 EXPRESS Rack PEHB Ethernet Interface A and T


Software and Computers Verification Requirement:

The PL interface to RIC Computer Software Configuration Item (CSCI) ethernet shall be compatible with IEEE-STD-802.3 (10 BASE-T section) TCP/IP protocol. (11.2.1)

The payloads ethernet interface data and file elements shall comply with Table 11-II of the IDD. (11.2.1)

Communications between the payload and the EXPRESS RIC CSCI across the logical ethernet interface through the PEHB shall include TCP/IP header, ethernet header, Sync word, EXPRESS Header (Table 11-IV), and data message. The command format is defined in Figure 11-6. The telemetry downlink packet shall include EXPRESS telemetry secondary header (Table 11-VI) on each packet, and the format shall be as defined in Table 11-VII. The Health and Status (H&S) shall be at 1.0 Hz rate with fixed length, fixed measurement location, and ECW as the first word. Payloads shall provide as the second word of H&S data an H&S Cycle counter as specified in the fourth paragraph of 11.2.3.6 of the IDD. A payload using parameter monitoring as the primary means of fire detection shall provide the capability to set the ECW word to indicate potential for fire. A payload not using parameter monitoring shall zero fill the ECW word. The message type for request service shall be as defined in Table 11-VIII. Status, Telemetry, and Health and Status data are defined in Table 11-IX. Payload messages (to the RIC) shall be as formatted as shown in the IDD Figures 11-5, and 11-5A (which includes any advisory messages to be displayed on a PCS on board the ISS or displayed by payload operations personnel). (11.2.1, 11.2.3.1, 11.2.3.3, 11.2.3.4, 11.2.3.5, 11.2.3.6, 11.2.3.7)


Using test data, verify by analysis that the payload using ethernet interfaces with the RIC CSCI meet all the IEEE 802.3 (10BASE-T section) TCP/IP protocol requirements as described in the IDD.

Using Suitcase Simulator (ScS) or payload GSE, verify by test that the payload using ethernet interfaces with the RIC CSCI are functionally compliant as described in the IDD.

Using Suitcase Simulator (ScS) (preferred) or payload GSE, verify by test that the payload can receive and process the correct command/response format from the Payload Executive Processor (PEP) and response/file transfer from RIC via PEHB ethernet interfaces as described in the IDD.Using Suitcase Simulator (ScS) (preferred) or payload GSE, verify by test that the payload can generate and transmit the correct telemetry and Health and Status format to the or laptop via PEHB ethernet interfaces as described in the IDD.




L-4.5 mo

B-84

SSP 53074-PVP, Draft 16/28/02



SW-ER-004 EXPRESS Rack PEHB Ethernet Interface A and T










L-4.5 mo


IEEE-STD-802.3SSP 52000-IDD-ERP: par 11.2.1, 11.2.3.1, 11.2.3.3, 11.2.3.4, 11.2.3.5, 11.2.3.6, 11.2.3.7

Note: The Suitcase Simulator (ScS) does not provide a flight-like simulation of the EXPRESS Rack PEHB/ethernet electrical characteristics.

B-85

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SW-ER-006 Software Safety Requirements for Payloads A



All software shall be considered 0-fault tolerant in the design of the payload hardware. (11.3)


Verify by analysis that software used for control of a safety hazard is used as no more than one inhibits.




L-4.5 mo


1. Same as the “Description of Verification Method” identified above.







L-4.5 mo


NSTS 1700.7, ISS Addendum: par 201.1ESSP 50005SSP 52000-IDD-ERP: par 11.3

B-86

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SW-ER-008 Payload Command Ground Interface A or T



Payload Uplink commands via EHS shall zero fill to meet the payload input S-Band minimum size requirement of 13 words, including the EXPRESS Header. (11.2.3.7)


Verify by analysis or test that the Uplink commands meet the payload input S-Band minimum 13 word requirement (including EXPRESS Header)




L-4.5 mo









L-6 mo


SSP 52000-IDD-ERP: par 11.2.3.7

B-87

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TH-ER-001 Touch Temperature A or A and I


Thermal Control Verification Requirement:

1. Payloads metallic surface temperatures which are exposed to crewmember’s bare skin contact shall be maintained between 0 °F (-18 °C) and 120 °F (49 °C) unless intention/incidental contact warrants provisions being applied as per paragraphs 5.1.1B and 5.1.1C. For non-metallic payload surfaces, the upper temperature limit for bare skin contact is higher than 120 °F and can be determined by using the method described in the NASA IVA Touch Temperature Safety interpretation letter, JSC MA2-95-048. (5.1.1A)

2. N/A

3. N/A


This requirement applies to all equipment whose surfaces are accessible to crew touch during operation.

An analysis shall be performed to verify the payload metallic surfaces are within the range of 0 °F (-18 °C) and 120 °F (49 °C) and that payload non-metallic surfaces are within the limits set by the NASA IVA Touch Temperature Safety interpretation letter, JSC MA2-95-048 or verify by inspection of the flight hardware that payload surfaces are provided with appropriate caution and warning labels, guards or insulation.

The lower temperature limit will be set by VRDS TH-ER-002, which is for the exposed surfaces, and will be the habitable volume dewpoint of 60 °F (16 °C). The use of guards is acceptable where surface temperatures are outside the range of -18 °C to 49 °C. This requirement is verified by thermal analysis of the payload surfaces bounded by worst-case extremes.

Verify by inspection that warning labels, guards, and insulation are installed as required.


Thermal analysis report to support rack level assessment.


L-7.5 mo





B-88

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TH-ER-001 Touch Temperature A or A and I






L-4.5 mo


NSTS 1700.7, ISS Addendum: par 222.3NSTS 18798: memo MA2-95-048SSP 52000-IDD-ERP: par 5.1.1A

B-89

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TH-ER-002 Condensation Prevention (All Equipment Surfaces) A or A and I



1. Payload surfaces shall be maintained above the maximum dewpoint temperature of 60 °F (16 °C) to prevent condensation in all ISS laboratories. (5.1.2)

2. A payload shall be designed to not cause condensation when exposed to a dewpoint of 40 to 60 °F (4.5 to 15.6 °C) and a relative humidity of 25 to 75 % except when condensation is an intended operation of the payload. (5.1.2.1)

When equipment which cools below the dewpoint (i.e., refrigerators/freezers, thermal electric devices, etc.) are opened for insertion or removal of items, some condensation around the periphery of the opening may temporarily occur. This is acceptable and may be wiped off. (5.1.2.1)


1. An analysis shall be performed to verify surface temperature remains above the dewpoint at all times to prevent condensation. The analysis must consider worst case for all mission phases. Analysis is required for equipment whose operation could result in decreasing temperature.

An inspection shall be performed of the as-built hardware to verify cooling lines and other payload equipment with surface temperatures below the dewpoint shall be provided with insulation to prevent condensation.

2. An analysis must be performed to verify temperatures and condensation potential and consider ISS humidity environments, including description of condensation collection system, illustration of all components of surfaces where condensation is most likely to occur and upper humidity limit in terms of dewpoint. Analysis must consider worst case for all mission phases.

An inspection shall be performed of the as-built hardware to verify cooling lines and other payload equipment with surface temperatures below the dewpoint are provided with insulation to prevent condensation or containment devices if condensation is a potential.


Thermal analysis report to support rack level condensation analysis.


L-11 mo




B-90

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TH-ER-002 Condensation Prevention (All EquipmentSurfaces)

A or A and I








L-4.5 mo


SSP 52000-IDD-ERP: par 5.1.2, 5.1.2.1

B-91

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TH-ER-003 Loss of Cooling A or A and T


Thermal Control Verification Requirement

Payloads using ISS EXPRESS Rack facility or payload-provided heat rejection systems (i.e., fans, pumps, water supply/flow, etc.) shall have the appropriate failure tolerance to prevent the hazard from occurring based on hazard category resulting from loss of cooling. The loss of cooling shall be considered the first failure in performing the hazard analysis if cooling is interrupted. (5.1.3)


An analysis of the hardware design shall be performed to determine the actual hazard and the hazard classification due to loss of cooling.

This requirement applies to all equipment using ISS EXPRESS Rack facility or payload-provided heat rejection systems (e.g., fans). The intent of this requirement is to verify that safety is not compromised in the event of failure of the cooling system. The requirement includes the avionics air system, cabin air system, moderate temperature loop, and equipment heaters, as well as payload-provided coolant loops or other heat rejection devices. In the case of equipment heaters, the payload shall verify that a safe condition exists in the event that equipment heaters fail “on.” The purpose of this requirement is to show that if loss of cooling results in overtemperature, overpressure, fire, explosion, release of hazardous or toxic materials, or damage, the failure is not propagated to other systems. If loss of cooling results in a hazard, the controls for shutdown must be verified by test.




L-4.5 mo









L-4.5 mo

B-92

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TH-ER-003 Loss of Cooling A or A and T


Applicable Documents and Notes

NSTS 1700.7, ISS AddendumSSP 52000-IDD-ERP: par 5.1.3

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TH-ER-004 Pressure Relief/Vent Valve Sizing A and T



Pressure relief devices, vent valves (PRV), and venting areas shall be set or sized such that the pressure differentials of captured volumes in sealed and semi-sealed enclosures shall not exceed the Maximum Design Pressure (MDP). (5.1.4)

Note: Equipment pressure relief valves and vent valves must not constitute a hazard to ground or flight operations. Where redundant relief valves are required, each valve must be sized to allow maximum flow in the event that one valve fails closed. The MDP is defined as the maximum pressure reached in a contained volume after consideration of any two credible failures (i.e., failure of Pressure Relief Valves (PRV), Heater Fail “ON,” etc.).


An analysis shall be performed to determine the system MDP.

Verify by analysis that capture volumes in payloads will survive worst-case decompression and recompression profiles and maintain positive margins of safety under MDP.Verify by test that all relief valves or other pressure relief devices operate correctly and have been properly set for the maximum possible flow for the given conditions.




L-4.5 mo









L-4.5 mo

B-94

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TH-ER-004 Pressure Relief/Vent Valve Sizing A and T



ICD-2-19001NSTS 1700.7, ISS Addendum: par 208.5SSP 52000-IDD-ERP: par 5.1.4

B-95

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TH-ER-005 On-Orbit Environmental Conditions A and/or T



The payload shall be compatible with the environmental conditions given in the IDD. (5.2)


Verify by analysis and/or test that operation of the payload will not result in an incompatibility under the specified environmental conditions.




L-4.5 mo









L-4.5 mo


NSTS 1700.7, ISS AddendumSSP 52000-IDD-ERP: par 5.2

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TH-ER-006 Passive Cooling/Heating of Cabin A, I



1. The sensible heat leak to the cabin air from the EXPRESS Rack payload either alone or together with the other EXPRESS Rack payloads simultaneously active shall not exceed the values in Table 5-VIII of SSP 52000 IDD. (5.3.1.1.2)

2. The ISS design value for the convective heat transfer coefficient is 0.20 Btu/hr °F ft2 for 14.7 psia or 0.17 Btu/hr °F ft2 for 10.2-psia cabin pressure. These values shall be used in thermal analysis/testing. (5.3.1.1.3)

3. All payload internal temperature requirements shall be met by heat rejection to only the cooling water loops and avionics air cooling circulated through the payload. Payloads do not need to be designed to the thermally isolated from the rack structure. Payloads shall not design to account for conducting payload heat to the rack structure. (5.3.1.3.7)


1. The requirement applies to parasitic heat losses from the payload, as well as active heat loads placed on the cabin air. Heat rejection across an interface is dependent on the temperature difference and interface conductance. These items are verified by thermal analysis. The power to be rejected across all interfaces is assumed to be equal to the total power consumed. Can be combined with TH-ER-015.

2. Verify by inspection/review of thermal analysis/test reports.

3. Verify by inspection/review of thermal analysis/test reports.



Thermal analysis report to support rack level cabin air heat exchange analysis.


L-4.5 mo

L-11 mo





B-97

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TH-ER-006 Passive Cooling/Heating of Cabin A, I





L-4.5 mo


SSP 52000-IDD-ERP: par 5.3.1.1.3, 5.3.1.3.7

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TH-ER-007 ISS/Middeck Cabin Cooling Interfaces A



1. When a payload provides an air circulation fan which internally circulates the air and discharges to the cabin, the maximum air outlet temperature shall not exceed 120 °F (48.9 °C). (5.3.1.2)

Note: For the middeck the maximum exhaust temperature is 120 °F (48.9 °C).

2. All payload internal temperature requirements shall be met by heat rejection to only the middeck cabin ambient air and active air cooling circulated through the payload. Payloads do not need to be designed to be thermally isolated from the Orbiter attach structure. Payloads shall not design to account for conducting payload heat to the Orbiter attach structure. By design on the Orbiter side, the conductive heat path through the Orbiter attach structure will be small (5%). (5.3.1.4.3)


1. The requirement applies to parasitic heat losses from the payload, as well as, active heat loads placed on the cabin air. Heat rejection across an interface is dependent on the temperature difference and interface conductance. These items are verified by thermal analysis. The power to be rejected across all interfaces is assumed to be equal to the total power consumed.

2. Verification shall be by thermal analysis of the payload hardware.



Thermal analysis report to support rack level cabin air heat exchange analysis.


L-4.5 mo

L-10 mo








L-4.5 mo

B-99

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TH-ER-007 ISS/Middeck Cabin Cooling Interfaces A



SSP 52000-IDD-ERP: par 5.3.1.2, 5.3.1.4.3

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TH-ER-008 Particulate(s) and Filters A or A and T, D and I



1. The payload cabin air cooling design will consider the possible ingestion of contamination from the cabin (e.g., 1.0 gram of lint-like material and/or 1.0 in2 material blockage in 16 days in the middeck); otherwise, the PD must provide protection from this contamination. The PD cooling system shall not contribute to the contamination of the cabin air or the avionics air loop. (5.3.1.2.1)

2. N/A


1. Verify by analysis or analysis and test of the PD cooling system to show that particulates, airflow, and payload filters/screens do not contaminate the EXPRESS Rack. If filters/screens are employed, the PD shall assess the impact of filter cake buildup and degraded airflow.

2. N/A




L-4.5 mo









L-4.5 mo


SSP 52000-IDD-ERP: par 5.3.1.2.1

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TH-ER-013 Payload Front Surface Temperature A



The EXPRESS Rack payload shall be designed not to exceed an average front surface temperature limit of 37 °C (98.6 °F) with a maximum temperature limit of 49 °C (120 °F). (5.3.1.1.1)


Analysis must consider worst case for all mission phases.




L-4.5 mo



2. Payloads remaining on-orbit past the original period of certification of the safety features or inhibits must perform a reverification of the activities as identified in the “Description of the Verification Method” identified above.






L-4.5 mo


SSP 52000-IDD-ERP: par 5.3.1.1.1

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EN-ER-001 Illumination Requirements-Lighting Design T and A and D


Environmental Verification Requirement:

1. Payload work surface specularity shall not exceed 20 percent. (10.2.1)

2. Payloads shall provide supplemental lighting at worksites to meet the illumination levels in Table 10-II. (10.2.2)

3. N/A

4. N/A

5. Medium payload operational tasks shall utilize the ISS portable utility light specified in JSC 27199. (10.2.5)


1. Verify by test that the payload work surface specularity does not exceed 20 percent.

2. Verify by analysis that the payload provides supplemental lighting at worksites to meet the illumination levels in Table 10-II.

3. N/A

4. N/A

5. Verify by analysis that medium payload operational tasks utilize the ISS portable utility light specified in JSC 27199.




L-4.5 mo


1. On-orbit subrack PL changeout: Same as the “Verification Requirements” above.



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EN-ER-001 Illumination Requirements-Lighting Design T and A and D



1. COC



L-4.5 mo


SSP 50005: par 8.13.3.1.2SSP 52000-IDD-ERP: par 10.2.1, 10.2.2, 10.2.5SSP 57000: par 3.12.3.4

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EN-ER-003 Radiation Requirements A



1. N/A

2. Materials and equipment shall not produce an unsafe condition or one that could cause damage to the ISS, EXPRESS Rack, or other payloads as a result of ionizing radiation-produced Single Event Effect (SEE). SEE analysis shall be performed per SSP 30512. (10.4.2)

3. Payloads shall not produce an unsafe condition or one that could cause damage to the ISS, EXPRESS Rack, or other payloads as a result of exposure to a radiation dose of 30 Rad (Si) per year or ionizing radiation. (10.4.3)


1. N/A

2. Verify by analysis that the payload materials and equipment do not produce an unsafe condition or one that could cause damage to the ISS, EXPRESS Rack, or other payloads as a result of ionizing radiation-produced SEE.

Verify by analysis that the payload SEE analysis is performed per SSP 30512.

3. Verification that payload equipment is designed to not produce an unsafe condition or one that could cause damage to the ISS, EXPRESS Rack, or other payloads shall be by analysis. An analysis of payload equipment shall be performed using the operational lifetime and parts characterization data to assure that the design meets the requirement when exposed to the ionizing radiation environment. For materials, existing literature from similar applications shall be analyzed to show that the materials meet the requirement when exposed to the specified radiation environment. The verification shall be considered successful when the analysis shows that the payload equipment will not produce an unsafe condition or one that could cause damage to the ISS, EXPRESS Rack, or other payloads when exposed to the specified environment. If analysis of the intended location in the ISS shows ionizing radiation exposure to be different than 30 Rad (Si) per year, the payload equipment shall design to the exposure determined by that analysis.



L-4.5 mo

B-105

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EN-ER-003 Radiation Requirements A



1. Same as the “Verification Requirements” above.




1. COC



L-4.5 mo


NSTS 13830: par 5.3.1.1NSTS 1700.7: par 212, 212.2SSP 50005: par 5.7.2.2.2.CSSP 52000-IDD-ERP: par 10.4.2, 10.4.3SSP 57000: par 3.9.3.3, 3.9.3.2

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EN-ER-004 Atmosphere Requirements A



1. The EXPRESS Rack payload consumption of atmospheric oxygen shall not exceed 0.10 kg per day (0.24 lbm per day). (10.5.1)

2. Chemical releases to the cabin air shall be in accordance with paragraphs 209.1a and 209.1b in NSTS 1700.7 Addendum. (10.5.2)


1. Verify by analysis that the payload consumption of atmospheric oxygen does not exceed 0.10 kg per day (0.24 lbm per day).

2. Verify by analysis that the payload chemical releases into the cabin air are in accordance with paragraphs 209.1a and 209.1b in NSTS 1700.7 and ISS Addendum.

Required Verification Data:1. Certificate of Compliance (COC) with the requirement.

2. Analysis report of O2 consumption.


L-4.5 mo

L-11 mo


1. On-orbit subrack PL changeout: Same as the “Verification Requirements” above.







L-4.5 mo

L-11 mo


NSTS 1700.7: par 209SSP 52000-IDD-ERP: par 10.5.1, 10.5.2SSP 57000: par 3.9.2.2, 3.9.2.3

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FP-ER-001 Fire Protection Interface Requirements A


Fire Detection/Suppression Verification Requirement:

Payloads shall meet the fire prevention requirements specified in NSTS 1700.7, ISS Addendum, paragraph 220.10. (14.1)


Verify by analysis included in the Safety Compliance Data Package that fire detection/suppression as described in the IDD is adequately addressed.




L-10 mo


1. Subrack payload changeout: Same as “Description of Verification Method” above.



Required Reverification Data:1. Certificate of Compliance (COC) with the requirement.



1, 2. Per PSRP Flight Safety Review schedule for new, reflight, or series PLs.


NSTS 1700.7, ISS Addendum: par 220.10SSP 52000-IDD-ERP: par 14.1

Note: The COCs are required to support/substantiate the Phase 3 Flight Safety Review Data Package for the integrated EXPRESS Rack.

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FP-ER-004 Payload Data Monitoring A and D


Fire Detection/Suppression Verification Requirements:

The EXPRESS payload parameter monitoring system for fire detection utilizes the PL MDM limit-checking services in combination with individual payload internal parameter monitoring to achieve the required functionality. EXPRESS payload data monitoring provides, as a minimum, the following: (1) The means for crew notification via computer display and via the ISS C&W (Class 2); (2) the means for payload location via computer display; (3) automatic (safe) powerdown of the payload when crew notification of out-of-limit conditions exist. Note: It must not be possible to automatically reapply power. (14.2)

1. All PD hardware when powered on shall output Health and Status data at 1 Hz continuously per Section 11. The content of the payload Health and Status/Safety data shall include payload subset ID (provided by ERO), payload service request, payload ECW word, and other PD Health and Status sensor information. (14.2A)

2. The payload shall be capable of monitoring key operating parameters (e.g., voltage, pressure, temperature, current, fan speed, etc.) and generating an ECW word as the first word of its Health and Status data that is sent to the EXPRESS Rack RIC. The exact set of data parameters to be monitored shall be negotiated jointly between the ISS program and the PD during the phased safety review process. The set of parameters shall be sufficient to characterize the fire potential while also reducing the possibility of false alarms. Preferably, data monitoring shall consist of multiple sensors of more than one type (i.e., two temperature sensors and two current monitors). Out-of-limit conditions which would constitute a potential fire or pyrolysis event would be defined as follows: When two or more sensors, of any type (predefined to provide a possible indication of fire or pyrolysis such as current, voltage, temperature, etc.) read out-of-limits simultaneously or within a relatively short time of each other. (14.2B)

3. The payload shall provide a logical combination of the monitored parameters and produce the ECW word 16-bit integer value as defined below: (14.2C)

A. 0 - No Problem

B. 1 - Advisory - System-initiated messages advising of a process status or other discrete event. Examples: Rendezvous solution complete, mass memory search for format in progress. Crew programmed reminder alerts keyed to time, orbit phase, bi-level state, parameter limit.

C. 3 - Warning - Conditions that require immediate correction to avoid loss or major impact to mission or potential loss of crew. Included are faults, failures, and out-of-tolerance conditions for functions critical to mission success.

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1. A. A demonstration/evaluation of the payload developer hardware shall be performed to verify the Health and Status data is formatted in accordance with the requirements in Section 11. Note: Suitcase Simulator (ScS) can be used in this testing.

B. An analysis of the Payload Developer software design shall be performed to verify that the Payload Developer Health and Status/Safety data includes the Payload Subset ID, Payload Service Requests, Payload ECW Word, and other Payload Developer Health and Status sensor information and the entire data set is less than or equal to 1248 bytes. A demonstration shall be performed to verify that this data is transmitted to the RIC. Note: The ScS can be used in this testing.

2. An analysis of the Payload Developer design shall be performed to verify whether or not the hardware item meets the requirements of being classified as a reference guidelines provided in NSTS 22648 sealed container.

3. A. An analysis of the Payload Developer design shall be performed to verify that the hardware design contains the sensors (multiple and of more than one type) which characterize the fire potential while also minimizing the possibility of false alarms. This set of sensor data must be approved by the JSC PSRP. A demonstration/evaluation of the hardware system shall be performed to verify the payload monitors the key operating parameters/sensors and transmits this telemetry to the EXPRESS Rack RIC. Note: The ScS can be used in this testing.

B. A demonstration shall be performed to verify that if any two sensors simultaneously or within 1 min detect out-of-limit conditions, the payload sets the ECW word to the correct status.

4. A. Verification of this requirement is fulfilled by performing the activities in “A.2” above. The ERO will provide the verification that the messages/data get transmitted for ISS computer display.

B. Verification of this requirement is fulfilled by performing the activities in “A.2” above. The ERO will provide the verification that the messages/data get transmitted for crew notification and the C&W system.

C. Verification of this requirement is fulfilled by performing the activities in “A.2” above. The ERO will provide the verification that once the out-of-limit condition message is transmitted from the Payload Developer hardware item, the RIC shuts off the SSPCM power source to the Payload Developer hardware item.

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L-10 mo


1. On-orbit subrack payload changeout. Electrical and software logic interfaces shall be verified following installation or re-installation.

2. On-orbit subrack payload changeout. Electrical and software logic interfaces shall be verified following installation or re-installation. On-orbit payload relocation.




1. Safety data package update.

2. Safety assessment of new location payload interfaces.




2. 30 days prior to location change.


NSTS 1700.7, ISS Addendum: par 220.10SSP 52000-IDD-ERP: par 14.2, 14.2A, 14.2B, 14.2C(1-3)


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FP-ER-005 Portable Fire Extinguisher Access Port I, A and/or T, D



The following requirements are applicable to powered payload equipment:

1. PFE Access Port: (14.3)

A. Payload equipment in a sealed container (per NSTS 1700.7) or has an inert atmosphere inside does not require a PFE port. (14.3A)

B. Payload equipment that interfaces with the EXPRESS Rack AAA cooling system does not require a PFE port. (14.3B)

C. Powered payload equipment which is active in the Orbiter middeck shall have a PFE access port. (14.3C)

D. Payload equipment that does not interface with the EXPRESS Rack AAA cooling system and has internal forced convection (i.e., cooling fan) shall have a PFE access port. This does not apply to payloads defined as sealed containers. (14.3D)

E. Payloads that do require a unique/dedicated PFE access port shall label the port to clearly distinguish it from the EXPRESS Rack PFE port. (14.3E)

F. N/A

G. Subrack payload volumes, payloads or aisle-mounted equipment requiring a PFE access port having a panel thickness less than or equal to 0.125 inch (3.175 mm) shall provide a PFE access port 0.5 inch (12.7 mm) or 1.0 inch (25.4 mm) in diameter. (14.3G)

H. N/A

2. PFE Characteristics: (14.3.1)

The PFE CO2 injection characteristics with which the payload shall be compatible are defined in SSP 30262:010, PFE Standard Interface Definition Document.

Notes:

1. Payloads are responsible to assess their payload volume(s) for potential hazards (i.e., loss of structural integrity and/or release of toxic or harmful materials as a result of PFE (CO2) discharge. Design solutions or controls must be identified and implemented if potential hazards have been identified.

2. The largest volume that can be extinguished by one PFE is 60 ft3 (a single fire event location, equivalent to a single ISPR).

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Fire Detection/Suppression Verification Requirements: (Continued)

3. PFE Port Dimensions: (14.3.2)

The fire suppressant access port shall be a circular hole 0.5 inches (1.27 cm) in diameter and shall be covered by a standard issue fire hole decal (P/N SDD32100397-003 or SDD32100397-004, Fire Hole Decal, per JSC 27260, Decal Process Document and Catalog).

Note: The use of a 0.5 inches diameter hole will allow the payload to maintain compatibility with both the PFE/ISS and the Orbiter middeck fire extinguisher systems.

4. PFE Access: (14.3.3)

EXPRESS Rack payloads that plan to use an ISS PFE shall provide a keepout envelope (including protrusions) sufficient to accommodate the PFE to the access port and shall be compatible with the PFE nozzle as shown in Figure 14-1.

5. PFE Quantity: (14.3.4)

Unless negotiated with ISS and agreed to by the PSRP, for each payload equipment item which requires a PFE access port, only one PFE access port shall be provided on the equipment item.


1. PFE Access Port:

A. An inspection of the as-built hardware shall be performed to verify that payload developer hardware defined as “sealed containers” or containing inert atmospheres does not have a PFE access port in accordance with SSP 30262:010.

B. An inspection of the as-built hardware shall be performed to verify that payload developer hardware interfacing with the EXPRESS Rack AAA cooling system does not have a PFE access port in accordance with SSP 30262:010.

C. An inspection of the as-built hardware shall be performed to verify that payload hardware which is planned to be powered in the middeck (either ascent, descent, or on-orbit) does have a PFE access port in accordance with SSP 30262:010.

D. An inspection of the as-built hardware shall be performed to verify that payload developer hardware not interfacing with the EXPRESS Rack AAA cooling system and having internal air circulation does have a PFE access port in accordance with SSP 30262:010.

F. N/A

G., H. An inspection of the as-built hardware shall be performed to verify that the payload PFE access port label size requirement is consistent with the panel thickness.

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Note: The payload user or organization may be required to verify by test that the unique configuration meets the fire suppression distribution requirements of the IDD. This is to assure that fire suppressant gets to all potential fire event locations.

2. Perform analysis and/or test to verify that discharge of a single ISS PFE into the payload volume does not pose added risk or introduce additional hazards as noted in paragraph 14.3.1.

3. An inspection of the as-built flight hardware shall be performed to verify the access port for hand-held fire extinguishers are 0.5 (or 1.0 +0.010) inches in diameter and covered by an approved decal.

4. An inspection and demonstration/evaluation shall be performed to verify the fire extinguisher access port is compatible with the PFE nozzle and has sufficient clearance envelope for the PFE.

5. An inspection of the as-built hardware shall be performed to verify that a single access port is available for each fire event location.

Note: Additional access ports, if required (as determined by analysis of the payload user/organization), may be requested and negotiated with the PSRP.

6. An inspection of this as-built hardware shall be performed to verify that payload volumes that have a PFE access port that will not be required for ISS provide a blank closeout.




L-10 mo


1. Subrack Payload changeout. Same as “Description of Verification Method” above.



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Applicable Documents and Notes: (Continued)

JSC 27260: total documentNSTS 1700.7, ISS Addendum: par 209.2; 220.10NSTS 22648: total documentSSP 30262:010: total documentSSP 50006: total documentSSP 52000-IDD-ERP: par 14.3A, 14.3B, 14.3C, 14.3D, 14.3E, 14.3G, 14.3.1, 14.3.2, 14.3.3, 14.3.4


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FP-ER-006 Fire Suppressant Distribution A or A and T



Fire event locations shall be designed such that the oxygen concentration in the free volume of the location is reduced to 10.5 percent or less by volume within 1 min after the discharge of a single PFE or the fire event location is surrounded by the CO2 within 1 minute after the discharge of a single PFE. (14.4)

Note: The requirements for achieving this 10.5 percent level for payloads interfacing to the EXPRESS Rack AAA system after discharge of the PFE into the EXPRESS Rack PFE port will be performed by the rack integrator. EXPRESS Rack payloads which do not interface with the AAA cooling loop shall perform their own analysis using the criteria of this paragraph.

Description of Verification Method:An analysis or a test/evaluation and analysis shall be performed to verify the identified fire event locations achieve 10.5 percent or less oxygen by volume within 1 min or less following discharge of fire suppressant (one PFE) or that rack internal payload volume is surrounded by CO2.




L-10 mo


1. Subrack Payload changeout: Same as “Description of Verification Method” above.







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FP-ER-006 Fire Suppressant Distribution A or A and T



NSTS 1700.7, ISS Addendum: par 220.10NSTS 22648: total documentSSP 52000-IDD-ERP: par 14.4


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MP-ER-001 Materials and Parts A and T and I


Materials and Parts Verification Requirement:1. The materials and parts used in the design of the payload hardware must accurately reflect the

as-built hardware.

2. N/A

3. Surface Cleanliness - Payloads shall conform to Visibly Clean-Sensitive (VC-S) cleanliness requirements as specified in SN-C-0005. (10.1B)

Payload design shall allow external surfaces to be cleaned with solvents and equipment available at the launch site (lint free cloths/swabs, isopropyl alcohol, demineralized water, etc.). Visibly clean “SENSITIVE” is the baseline level for all payloads. (10.1A)

4. Stress Corrosion Cracking - Metallic materials (especially those considered to be structure members, such as payload structures, support bracketry, and mounting hardware, and those whose failure could result in a critical or catastrophic hazard) which have a high resistance to SCC according to the criteria of MSFC-SPEC-522 shall be used preferentially. (13.1, 13.1.1)

Note: All materials used in fracture-critical structures must have a documented audit trail that assures only materials specified by the drawing have been used. (13.4)

5. Materials Compatibility - The use of materials, chemicals, and fluids which could create a toxic or hazardous situation for the crew, or which could contribute to the deterioration of hardware in service, shall be given special consideration as to adequate containment and compatibility. (13.1, 13.1.2)

6. Flammability, Nonmetallic Materials - Payload materials shall be nonflammable or self-extinguishing per the test criteria of NHB 8060.1. (13.1, 13.1.3, 14.1.1)

7. Toxic Offgassing - All flight hardware located in habitable areas shall meet the toxicity offgassing acceptance requirements of NASA-STD-6001, Test 7. (13.1, 13.1.4)

8. N/A

9. N/A


1. N/A

2. N/A

3. Verify by inspection that the payload exterior and accessible interior surfaces are in accordance with VC-S cleanliness requirements as specified in JSC SN-C-0005. An inspection of the cleanliness documentation shall be performed to show the exterior and accessible interior surfaces meet the VC-S requirements. The verification will be considered successful when the

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inspection shows the payload exterior and accessible interior surfaces meet the VC-S cleanliness requirements specified in JSC SN-C-0005. Verify by analysis that all payload equipment exterior and accessible interior surfaces are capable of being cleaned with solvents and equipment at the ISS launch sites and on-orbit. A compatibility analysis shall be performed to determine if the payload exterior and accessible interior surfaces can be cleaned with solvents and equipment at the ISS launch sites and on-orbit. The verification shall be considered successful when the analysis shows the payload exterior and accessible interior surfaces are capable of being cleaned with solvents and equipment at the ISS launch sites and on-orbit.

4. Verify by analysis that no stress corrosion susceptible materials per MSFC-SPEC-522 are used, or that Material Usage Agreements (MUA) have been approved for their use. The analysis shall compare the materials and parts list and the drawings with the materials listed in MSFC-SPEC-522. The verification shall be considered successful when the analysis shows that no stress corrosion susceptible materials per MSFC-SPEC-522 are used, or that MUAs have been approved for their use.

5. Verify by analysis or test that hazardous materials are compatible with their containment system materials of construction per the requirements of NSTS 1700.7, ISS Addendum, paragraphs 209.1a and 209.1b, and/or are compatible with their use environment.

Verify by analysis or test that sample materials are compatible with their containment system. An acceptable test method is NASA-STD-6001, Test 15.

Verify by analysis or test that the nominal/planned release of materials to the cabin does not constitute a hazard or could be detrimental to other materials in the cabin.

6. Verify by inspection that the materials used in the design of the payload hardware accurately reflect the as-built configuration. Verification of payload hardware flammability shall be by inspection. The inspection shall determine whether the payload materials either meet the flammability acceptance criteria of NASA-STD-6001 per the worst-case use conditions of NSTS 1700.7, ISS Addendum, or that sufficient justification documentation (such as MUAs) for flammable materials used in quantities as noted in NSTS 1700.7, ISS Addendum, has been presented and approved to allow their use. The verification shall be considered successful when the inspection shows that the payload materials are either nonflammable or self-extinguishing per NHB 8060.1, or that sufficient justification has been approved for their use.

7. Verification of toxic offgassing by payload hardware shall be by test. A test shall be conducted on all payload hardware per the conditions and criteria of NASA-STD-6001, Test 7, to determine the suitability of the payload nonmetallic materials and assembled articles used in crew

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compartment environments with respect to toxic offgassed products. The verification shall be considered successful when the test results show the payloads in habitable areas meet the toxic offgassing acceptance criteria of NASA-STD-6001, Test 7.

8. N/A

9. N/A


1. Certificate of Compliance (COC) with the requirements. The COC must include the concurrence of an ISS Program-approved Materials and Processes organization (e.g., the Materials and Processes organizations of NASA field centers which participate in the Materials and Processes Intercenter Agreement).

2. Analysis and test reports to support rack level analysis of nominal/planned release of materials.

3. Analysis and drawings to support rack-level analysis of flammability.


L-4.5 mo

L-7 mo

L-7 mo


1. On-orbit subrack payload changeout: Same as the “Description of Verification Requirement” identified above.




1, 2. Same as “Required Verification Data” identified above.


L-4.5 mo

L-9 mo

L-9 mo

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JSC SN-C-0005MSFC-SPEC-250: total document MSFC-SPEC-522: total document MSFC-HDBK-527/JSC 09604: total document NASA-STD-6001: sec 4.1, 4.7, 4.15NSTS 1700.7: par 208.3, 209.1, 209.1A, 209.1B, 209.3, 220.10NSTS 1700.7, ISS Addendum: par 208.3, 209.1, 209.1A, 209.1B, 209.2B, 209.3, 220.10NSTS 22648: total documentSSP 30233: total document SSP 52000-IDD-ERP: par 10.1A, 10.1B, 13.1, 13.1.1, 13.1.2, 13.1.3, 13.1.4, 13.4, 14.1.1SSP 52000-PAH-ERP: par 4.8.4


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HF-ER-001 Handles, Restraints, Tether Points, and Captive Parts

I, I and D, A and I


Human Factors Verification Requirement:

1. All removable or portable items that cannot be grasped with one hand per Figure 12-1 of SSP 52000-IDD-ERP shall be provided with handles or other suitable means of grasping, tethering, carrying, and restraining. Hand size dimensions are provided in Table 12-Ia. Figure 12-1a shows where the measurements are taken for hand size dimensions. (12.1.1)

2. Handles and grasp area shall be placed on the accessible surface of an item consistent with the removal direction. (12.1.2)

3. IVA handles for movable or portable units shall be designed in accordance with the minimum applicable dimensions in Figure 12-1 of SSP 52000-IDD-ERP. (12.1.3)

4. IVA clearances shall be provided between handles and obstructions consistent with dimensions given in Figure 12-1 of SSP 52000-IDD-ERP. (12.1.4)

5. N/A

A. N/A

B. N/A

C. N/A

6. Tether points used on portable items for temporary stowage or placement purposes shall meet the structural margin of safety requirements specified in SSP 52005. These tether points shall be physically compatible with standard ISS tethers, or the PD shall provide the necessary tethers. (12.1.6)

7. All PD-provided stowage items shall have a method of securing them in place during on-orbit activities. Hook Velcro patches shall be placed on all stowage items for the temporary stowage/placement purposes. These patches shall be no more than 4 in2 in area and separated by a minimum of 2 inches. The size and shape should be consistent with the dimensions of the stowage item. Multiple Velcro patches on a single stowage item are allowed. (12.1.7)

8. Payloads and payload equipment shall be designed in such a manner to ensure that all unrestrained parts (e.g., locking pins, knobs, handles, lens covers, access plates or similar devices) that may be temporarily removed on-orbit will be tethered or otherwise held captive. Items not physically held captive shall provide a restraint capability shall provide a restraint capability such as tether, Velcro, etc. (12.1.8)

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I, I and D, A and I



1. Each piece of payload equipment (especially detachable/removable items) must have its volume calculated to determine the volume. Items which are equal to or greater than 1 ft3 must have a handle or other suitable means for grasping, tethering, handling, carrying, and securing as a part of the design. The hardware must be inspected to verify that the as-built hardware meets the drawings and a handle or other suitable means for grasping, tethering, handling, carrying, and securing is present.

2. For each piece of payload equipment (especially detachable/removable items) determined to be equal to or greater than 1 ft3 and requiring a handle, the handle must be located on the accessible surface and consistent with the removal direction. The hardware must be inspected to verify that as-built hardware meets the drawings. A demonstration to verify that the handle is located in the removal direction must be performed.

3. For each piece of payload equipment (especially detachable/removable items) determined to be equal to or greater than 1 ft3 and requiring a handle, the handle must be designed in accordance with the minimum applicable dimensions in Figure 12-1 of SSP 52000-IDD-ERP. The hardware must be inspected to verify that the as-built hardware meets the drawings.

4. For each piece of payload equipment (especially detachable/removable items) must have its volume calculated to determined to be equal to or greater than 1 ft3 and requiring a handle, clearances must be provided for in the payload design drawings the handle between handles and obstructions consistent with dimensions as given in Figure 12-1 of SSP 52000-IDD-ERP. The hardware must be inspected to verify that the as-built hardware meets the drawings. A demonstration must be performed to verify that the IVA clearances are sufficient to grasp handles as required to remove, transfer, replace, operate, and maintain the payload equipment.

5. For each piece of payload equipment (especially detachable/removable items) determined to be equal to or greater than 1 ft3 and requiring a handle and using a nonfixed-type handle, the requirements for stop position, one-handed operation, and indication of status (locked/unlocked) must be included in the design. The hardware must be inspected to verify that the as-built hardware meets the drawings. A demonstration must be performed to verify the above three requirements have been satisfied.

6. A. Analysis: See VRDS ST-ER-001

B. Inspection: The tether point(s) must be designed to be compatible with the ISS-provided tethers shown in SSP 52000-IDD-ERP (Figures 3-29 and 3-30) and also that requirement for clearances is met. The hardware must be inspected to verify that the as-built hardware meets the drawings.

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I, I and D, A and I


Description of Verification Method: (Continued)7. A. Each stowage item must be inspected for inclusion of securing methods for on-orbit

activities.B. If velcro is selected, the patch must be inspected to verify it is less than 4 in2 in size.

8. All of the payload unrestrained parts that may be temporarily removed must be identified. Verify by inspection that payloads and payload equipment are designed and fabricated to have provisions to ensure that all of the unrestrained parts will be tethered or otherwise held captive. For those parts not physically held captive an inspection must be performed to verify alternative restraint provisions are present in the hardware design.



L-4.5 mo


1. Same as “Verification Requirement” above.2. Payloads remaining on-orbit past the original period of certification of the safety features or



Required Reverification Data:1. Certificate of Compliance (COC) with the requirement.2. Same as “Required Verification Data” identified above.

Data Submittal Dates:L-4.5 mo L-4.5 mo


STS 1700.7, ISS Addendum: par 208SSP 52000-IDD-ERP: par 12.1.1, 12.1.2, 12.1.3, 12.1.4, 12.1.6, 12.1.7, 12.1.8SSP 52005Notes:

1. Delivery date assumes 30 days prior to turnover to KSC and PD hardware must be turned over to KSC at L-5 months.

2. Analysis verification for item 6.A is covered on VRDS ST-ER-001.

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HF-ER-002 Strength and Force Requirements A or D



1. Grip strength required to remove, replace, and operate EXPRESS Rack payload hardware momentary and sustained grip strength required shall be less than the strength values for the 5 th

percentile female defined as 50 percent of the strength values shown in Figure 12-2 of SSP 52000-IDD-ERP. This applies for operation and control of EXPRESS Rack payload hardware equipment. (12.2A(1))

2. Linear forces required to operate or control EXPRESS Rack payload hardware shall be less than the strength values for the 5th percentile female (defined as 50 percent of the strength values shown in SSP 52000-IDD-ERP, Figure 12-2 and 60 percent of the strength values shown in SSP 52000-IDD-ERP, Figure 12-3). (12.2A(2))

3. Forces/torques required to operate or control EXPRESS Rack payload hardware shall be less than the strength values for the 5th percentile female (defined as 60 percent of the calculated 5th percentile male capability shown in SSP 52000-IDD-ERP, Figure 12-4). This applies for operation and control of EXPRESS Rack payload hardware equipment. (12.2.A(3))

4. Forces required for maintenance of EXPRESS Rack payload hardware shall be less than the strength values for the 5th percentile male as shown in SSP 52000-IDD-ERP, Figures 12-3, 12-4, 12-5, and 12-6. (12.2B)

5. N/A


1. A demonstration or analysis must be performed to measure the required grip strength to determine it is less than the strength values for the 5th percentile female.

2. A demonstration or analysis must be performed to measure the required linear forces to determine they are less than the strength values for the 5th percentile female.

3. A demonstration or analysis must be performed to measure the required torques to determine they are less than the strength values for the 5th percentile female.

4. A demonstration must be performed to measure the required forces for maintenance operations to determine they are less than the strength values for the 5th percentile male.

5. N/A




L-4.5 mo

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HF-ER-002 Strength and Force Requirements A or D










L-4.5 mo


SSP 52000-IDD-ERP: par 12.2A(1), 12.2A(2), 12.2A(3), 12.2BSSP 57010, ST-005

Notes:

1. Grip strength requirement applies for operation and control of EXPRESS Rack payload hardware equipment.

2. The submittal date assumes 30 days prior to turnover to KSC and PD hardware must be turned over to KSC at L-5 months.

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HF-ER-003 Full Size Range, Volume and AccessibilityAccommodation

A or D, A, A or D, and D or A and I



1. N/A

2. The EXPRESS Rack payload shall provide volume accessibility and clearance for the crew to perform installation, operations, and maintenance tasks including clearance for hand access, tools and equipment used in these tasks within the PD volume. Items which require use of volume outside of the individual PD volume should be identified to the rack integrator/ERO for consideration in an integrated assessment. (12.3.1)

3. The EXPRESS Rack payload shall: (12.3.2)

A. Be geometrically arranged to provide physical and visual access for all installation, operations, and maintenance tasks. Requirements for visual access are shown in Table TBD#34. Payload ORUs should be removed along a straight path until they have cleared the surrounding structure.

B. Provide IVA clearances for finger access as given in Figure 12-7 of SSP 52000-IDD-ERP for conditions without visual access.


1. N/A

2. An analysis or demonstration shall be performed to show there is adequate volume for the crew to perform installation/operations/maintenance tasks and also accommodate required tools/equipment in the payload volume.

3. A. An analysis or demonstration shall be performed to show/assess that the payload configuration is compatible with all tasks (removal, replacement, operation, and maintenance) and that physical and visual access are provided.

B. An inspection and demonstration or analysis must be performed to show that the payload has provided IVA clearances for one-hand, two-hand, and finger access as given in Figure 12-8 of SSP 52000-IDD-ERP for all tasks (removal, replacement, operation, and maintenance). The hardware must be inspected to verify that the as-built hardware meetsthe drawings.




L-4.5 mo

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HF-ER-003 Full Size Range, Volume and AccessibilityAccommodation

A or D, A, A or D, and D or A and I










L-4.5 mo


SSP 50005: sec 3SSP 52000-IDD-ERP: par 12.3.1, 12.3.2A-B

Note: The submittal date assumes 30 days prior to turnover to KSC, and PD hardware must be turned over to KSC at L-5 months.

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HF-ER-004 Equipment Mounting D or A and I



Equipment items used during nominal operations and planned maintenance shall be designed, labeled, or marked to support proper installation. (12.4.1)


An analysis or demonstration shall be performed to show/assess that all required items are designed, labeled, or marked to support proper installation.

For use of alignment marks, an inspection shall be performed of the as-built hardware to verify alignment mark configuration (size, orientation, position, etc.)




L-4.5 mo









L-4.5 mo




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HF-ER-005 Drawers and Hinged Panels A or T and I



EXPRESS Rack payload ORUs or exchangeable items which are pulled out of their installed positions for routine checkout shall be mounted on equipment drawers or on hinged panels. Such drawers or hinged panels shall remain in the “open” position without being supported by hand. (12.4.2)


An inspection shall be performed to show that all required items (ORUs, exchangeable items, etc.) are mounted in equipment drawers or on hinged panels.

An analysis shall be performed to show that the drawers or hinged panels will stay in the “open” position without being supported. This could also be done via test, but the drawer/panel must only remain “open” in a zero-g environment.




L-4.5 mo









L-4.5 mo




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HF-ER-006 Alignment, Align Marks, Guide Pins I



1. N/A

2. Mating parts shall have alignment marks in a visible location during mating or guide pins (or their equivalent). (12.7.12)

3. A. Both halves of mating connectors shall display a code or identifier which is unique to thatconnection. (12.5.3A)

B. N/A


1. An inspection or demonstration of the as-built hardware shall be performed to verify alignment features are in place and operated properly for blind mate connectors.

2. An inspection/evaluation of the as-built hardware (PD connectors) shall be performed to verify that alignment marks, guide pins, or their equivalent are applied to mating parts. Vendor certification is acceptable.

3. An inspection/evaluation of the as-built hardware (all PD mating connectors) shall be performed to verify that both halves of mating connectors have a code/identifier which is unique to that connection and this code/identifier is visible whether connected or disconnected.




L-4.5 mo









L-4.5 mo

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HF-ER-006 Alignment, Align Marks, Guide Pins I



SSP 52000-IDD-ERP: par 12.7.12, 12.5.3A

Notes:

1. The submittal date assumes 30 days prior to turnover to KSC, and PD hardware must be turned over to KSC at L-5 months.

2. Keying of a connector is a considered equivalent to a guide pin.

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HF-ER-011 Labeling Design Requirements I



Each switch control shall be labeled. (12.5)


An inspection of the as-built hardware (payload equipment item) shall be performed to verify that each switch control is labeled.


Certificate of Compliance with the requirement.


L-4.5 mo






1. Certificate of Compliance with the requirement.



L-4.5 mo


JSC 36044SSP 50254SSP 52000-IDD-ERP: 12.5

Notes:

1. Delivery dates assumes 30 days prior to turnover to KSC and PD hardware must be turned over to KSC at L-5 months.

2. Upper and lower case letters should be used as appropriate.

3. The materials of construction for the labels to be evaluated for useful life and usage using the environments in SSP 52000-IDD-ERP.

4. Helvetica is the preferred font.

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HF-ER-014 Color I



Payloads shall select interior colors in accordance with the requirements of SSP 52000-IDD-ERP, Table 12-I. (12.5.1)


An inspection/evaluation of the as-built hardware (PD equipment item/decal/placard/label) shall be performed to verify that colors are per SSP 52000-IDD-ERP, Table 12-I.




L-4.5 mo


No reverification required.


None Required.


N/A


FED-STD-595SSP 52000-IDD-ERP: par 12.5.1

Note: Delivery date assumes 30 days prior to turnover to KSC, and PD hardware must be turned over to KSC at L-5 months.

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HF-ER-017 Controls Spacing Design I, I or D



1. All spacing between controls and adjacent obstructions shall meet the minimum requirements as shown in SSP 52000-IDD-ERP, Figure 12-9, “Control Spacing Requirements for Ungloved Operation.” (12.6.1)

2. Payload provided protection devices shall not cover or obscure other displays or controls. (12.6.2.2)

3. Barrier guard spacing shall adhere to the requirements for use with the toggle switches, rotary switches, and thumbwheels as shown in SSP 52000-IDD-ERP, Figure 12-9, “Control Spacing Requirements for Ungloved Operation,” and Figure 12-10, “Rotary Switch Guard.” (12.6.2.4)


1. An inspection/evaluation of the as-built hardware (all PD controls) shall be performed to verify that there is sufficient spacing per Figure 12-9 between adjacent controls and adjacent obstacles.

2. An inspection/evaluation or demonstration of the as-built hardware (all PD controls and protection devices) shall be performed to verify that protective devices when installed do not cover or obscure other displays or controls.

3. An inspection/evaluation of the as-built hardware (all PD controls barrier guard spacing) shall be performed to verify that the spacing is per Figures 12-9 and 12-10.




L-4.5 mo









L-4.5 mo

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HF-ER-017 Controls Spacing Design I, I or D



SSP 52000-IDD-ERP: par 12.6.1, 12.6.2.2, 12.6.2.4


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HF-ER-018 Accidental Actuation - Protection I or D, I



Requirements for mitigating accidental actuation of controls shall be selected from below: (12.6.2.1)

1. A. Locate and orient the controls so that the operator is not likely to strike or move them accidentally in the normal sequence of control movements.

B. Recess, shield, or otherwise surround the controls by physical barriers. The control shall be entirely contained within the envelope described by the recess or barrier.

C. Cover or guard the controls. Safety or lock wire shall not be used.

D. Cover guards when open shall not cover or obscure the protected control or adjacent controls.

E. Provide the controls with interlocks so that extra movement (e.g., lifting switch out of locked detent position) or the prior operation of a related or locking control is required.

F. Provide the controls with resistance (i.e., viscous or coulomb friction, spring-loading, or inertia) so that definite or sustained effort is required for actuation.

G. Provide the controls with a lock to prevent the control from passing through a position without delay when strict sequential actuation is necessary (i.e., the control moved only to the next position, then delayed.)

2. N/A

3. N/A

4. N/A

5. N/A


1. An inspection/evaluation or demonstration of the as-built hardware (all PD controls) shall be performed to verify that protective methods have been implemented from the list above to prevent accidental actuation.

2. N/A

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HF-ER-018 Accidental Actuation - Protection I or D, I



3. N/A

4. N/A

5. N/A




L-4.5 mo









L-4.5 mo


SSP 52000-IDD-ERP: par 12.6.2.1, 12.6.2.1B-D

Notes:

1. Infrequently used controls (i.e., those used for calibration) should be separated from frequently used controls. Lever lock switches or switch covers are strongly recommended for switches related to mission success. Switch guards may not be sufficient to prevent accidental actuation.

2. Displays and controls used only for maintenance and adjustments which could disrupt normal operations if activated should be protected during normal operations (e.g., by being located separately or guarded/covered).

3. Delivery date assumes 30 days prior to turnover to KSC, and PD hardware must be turned to KSC and L-5 months.

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HF-ER-020 Toggle Switches I



Dimensions for a standard toggle switch shall conform to Figure 12-13 of SSP 52000-IDD-ERP, “Toggle Switches.” (12.6.4)


An inspection/evaluation of the as-built hardware (toggle switches) shall be performed to verify that it meets the dimensions of Figure 12-13 of SSP 52000-IDD-ERP.




L-4.5 mo








L-4.5 mo




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HF-ER-022 Electrical Connectors Design (One-Hand Operation, Ease of Disconnect, Self-Locking)

D



1. All connectors, whether operated by hand or tool, shall be designed so they can be mated/demated using either hand. (12.7.5)

A. Nominal Operations - It shall be possible to mate/demate individual connectors without having to remove or mate/demate other connectors. (12.7.6A(1))

B. Maintenance Operations - It shall be possible to mate/demate individual connectors without having to remove or mate/demate connectors on others ORUs or payloads. (12.7.6A(2))

C. Electrical connectors and cable installations shall permit disconnection and connection without damage to wiring connectors. (12.7.6B)

2. Electrical connectors which are mated/demated during nominal operations shall require no more than two turns to disconnect. (12.7.7A)

3. Electrical connectors which are mated/demated during ORU replacement operations only shall require no more than six turns to disconnect. (12.7.7B)

4. Payload electrical connectors shall provide a self-locking feature. (12.7.8)


A demonstration/evaluation of the as-built hardware (PD equipment) shall be performed to demonstrate and verify:

1. A. All connectors can be accessed by either hand.

B. All connectors can be mated/demated by either hand.

C. No other connectors shall be required to be disconnected to gain access to another connector.

D. No damage to wiring connectors is to be sustained due to connection/disconnection.

2. A demonstration/evaluation of the as-built hardware (PD connectors) shall be performed to verify that each connector which is mated/demated during nominal operations requires no more than two turns to disconnect. Vendor certification is acceptable.

3. A demonstration/evaluation of the as-built hardware (PD connectors) shall be performed to verify that each connector which is mated/demated during ORU replacement operations only requires no more than six turns to disconnect. Vendor certification is acceptable.

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HF-ER-022 Electrical Connectors Design (One-Hand Operation, Ease of Disconnect, Self-Locking)

D



4. An inspection/evaluation of the as-built hardware (PD connectors) shall be performed to verify that each connector has a self-locking feature. Vendor certification is acceptable.




L-4.5 mo









L-4.5 mo


SSP 52000-IDD-ERP: par 12.7.5, 12.7.6A(1), 12.7.6A(2), 12.7.6B, 12.7.7A, 12.7.7B, 12.7.8


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HF-ER-023 Electrical Connectors Design - Protection, Shape, and Arc Containment

I or A, A and I


Human Factors Verification Requirement:1. Protection shall be provided for all demated connectors against physical damage and

contamination. (12.7.2)2. Subrack connectors shall use different connector shapes, sizes, or keying to prevent mating

connectors when lines differ in content. (12.7.9)3. Pins shall be identified in each electrical plug and each electrical receptacle either by marking the

pins or by an accompanying reference table. At least every 10th pin must be labeled. (12.5.4)4. Electrical connector plugs shall be designed to confine/isolate the mate/demate electrical arcs or

sparks. (12.7.3)

Description of Verification Method:1. An inspection/evaluation or analysis of the as-built hardware (PD equipment) shall be performed

to verify that a protection device is provided for demated connectors.2. An analysis and inspection/evaluation of the as-built hardware (PD connectors) shall be

performed to verify that for lines that differ in content, connectors have different shapes or are physically incompatible. Vendor certification is acceptable.

3. An inspection/evaluation of the as-built hardware (all PD connectors) shall be performed to verify that both the plug and receptacle pins are identified. If identification is not possible a reference table shall be developed for inclusion in the operating procedures.

4. An analysis and inspection/evaluation of the as-built hardware (PD Connectors) shall be performed to verify that the electrical connector plugs adequately confine/isolate the mate/demate electrical arcs or sparks. Vendor certification is acceptable.




L-4.5 mo(See Note 2)





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HF-ER-023 Electrical Connectors Design - Protection, Shape, and Arc Containment

I or A, A and I








SSP 52000-IDD-ERP: par 12.5.4, 12.7.2, 12.7.3, 12.7.9

Notes:

1. The submittal date assumes 30 days prior to turnover to KSC, and PD hardware must be turned over to KSC at L-5 months.

2. If a reference table is selected as the method of identifying pins, it must be available to document in the PODF.

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HF-ER-024 Arrangement and Orientation for Connectors I and D or A, A or I



1. Space between connectors and adjacent obstructions shall be a minimum of 1 in (25 mm) for IVA access. (12.7.4A)

2. Connectors in a single row or staggered rows which are removed sequentially by the crew (IVA) shall provide 1 in (25 mm) of clearance for other connectors and/or adjacent obstructions for 270 degrees of sweep around each connectors beginning at the start of its removal/replacement sequence. (12.7.4B)

3. N/A


1. An inspection/evaluation and demonstration or analysis of the as-built hardware (PD connector layout) shall be performed to verify that the space between connectors and adjacent obstructions are 1 in or greater.

2. An inspection/evaluation and demonstration or analysis of the as-built hardware (PD connector layout) shall be performed to verify that for connectors in a single row or staggered rows provide 1 in of clearance and 270 degrees of sweep around each connector beginning at the start of its removal/replacement sequence. The payload flight procedures must be reviewed to determine the installation/removal sequence of connectors.

3. N/A




L-4.5 mo





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HF-ER-024 Arrangement and Orientation for Connectors I and D or A, A or I






L-4.5 mo


SSP 52000-IDD-ERP: par 12.7.4A, 12.7.4B


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HF-ER-028 Waste Management I



General use equipment, including provisions for on-orbit treatment, packaging/labeling, and stowage of trash, will be provided as Government-Furnished Equipment (GFE) for the use of all on-orbit payloads. Definition of this equipment is shown in TBD#24. Any payload-unique requirement necessitating waste management provisions other than that provided as GFE will be negotiated and documented in the payload’s unique ICD. (12.10)


Awaiting ISS Program Office Action. The requirement in SSP 52000-IDD-ERP is not defined. This requirement and its associated VRDS will be updated when the requirement is updated in SSP 57000.


The data required for verification of this requirement is still in work.


Under review.



2. Payloads remaining on-orbit past the original period of certification of the safety features or inhibits must perform the same verification activities as identified in the “Description of the Verification Method” identified above.






Under review.


SSP 52000-IDD-ERP: par 12.10SSP 57000E

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HF-ER-030 Other Non-Threaded Fasteners I or D



1. An indication of correct engagement (hooking, latch fastening, or proper positioning of interface parts) of non-threaded fasteners shall be provided except for screw-type fasteners. (12.12.1)

2. N/A

3. N/A

4. N/A


1. An inspection/evaluation or demonstration of the as-built hardware (payload equipment) must be performed to verify that all non-screw type fasteners are equipped with an indication of correct engagement.

2. N/A

3. N/A

4. N/A




L-4.5 mo









L-4.5 mo

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HF-ER-030 Other Non-Threaded Fasteners I or D





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HF-ER-031 Mounting Bolts and Fasteners I, I and A, D, A and I or D



1. Clearance around fasteners to permit fastener hand threading (if necessary) shall be a minimum of 0.5 inches for the entire circumference of the bolt head and a minimum of 1.5 inches over 180 degrees of the bolt head and provide the tool handle sweep as seen in Figure 12-14 of SSP 52000-IDD-ERP. (12.12.2)

2. When several fasteners are used on one item they shall be of identical type. (12.12.3)

3. All fasteners planned to be installed and/or removed on-orbit shall be captive when disengaged. (12.12.4)

4. Only right-handed threads shall be used. (12.12.6)

5. A. Hex-type external or internal grip or combination head fasteners shall be used where on-orbit crew actuation is planned (e.g., ORU replacement). (12.12.9A)

B. If a smooth surface is required, flush or oval head internal hex grip fasteners shall beused for fastening. (12.12.9B)

C. Slotted fasteners shall not be used to carry launch loads for hard-mounted equipment. Slotted fasteners are allowed in non-structural applications (e.g., computer data connectors, stowed commercial equipment). (12.12.9C)

6. Fasteners planned to be removed or installed on-orbit shall be designed and placed so they can be mated/demated using either hand. (12.12.10)

7. IVA fasteners shall be separated to provide hand and tool clearance in accordance with SSP 52000-IDD-ERP, Figure 12-14. (12.12.11)

8. When payloads are attached to PMPs, single adapter plates, double adapter plates or VPMPs, clearance shall be provided for the tool to engage the payload mounting bolts from the cabin. Minimum clearance required shall be 0.5 in for the entire circumference of the bolt head and a minimum of 1.5 in over 180 degrees of the bolt head and provide tool handle sweep per Figure 12-14 of SSP 52000-IDD-ERP. (3.4.3.5)

9. Payloads shall be designed to allow access to the payload mounting bolts as defined in paragraphs 3.4.3.6 through 3.4.3.6.3 of SSP 52000-IDD-ERP. (3.4.3.5.1B)

2. Payload equipment shall not require the use of special tools for payload removal unless the tool is supplied by the PD. PDs are encouraged to use standard metric/English fasteners and tools. (3.4.3.5.1C)

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Description of Verification Method:1. An inspection/evaluation of the as-built hardware (payload mounting bolts and fasteners) must

be performed to verify that spacing between fasteners and other surfaces are in accordance with the minimum dimensions identified in SSP 52000-IDD-ERP, Figure 12-14.

2. An inspection/evaluation of the as-built hardware (payload mounting bolts/fasteners) must be performed to verify that all fasteners used on the same item are identical.

3. An inspection/evaluation of the as-built hardware (payload items) must be performed to verify that any fasteners which must be removed on-orbit are held captive.

4. An inspection/evaluation of the as-built hardware (payload items) must be performed to verify that any threaded fasteners use right-handed threads.

5. A review of the flight crew procedures including Malfunction Procedures and IFMs must be performed to identify the fasteners with planned on-orbit use. The following inspections must be made on the fasteners:A. An inspection/evaluation of the as-built hardware (payload items) must be performed to

verify that fasteners with planned on-orbit use of hex-type external or internal grip or combination head fasteners.

B. An inspection/evaluation of the as-built hardware (payload items) must be performed to verify that any flush or oval head internal hex grip fasteners are used only when a flush surface is required (e.g., bottom of ISIS drawers).

C. An inspection/evaluation of the as-built hardware (payload items) must be performed to verify that there are no straight-slot fasteners used to carry launch loads.

6. A review of the flight crew procedures including Malfunction Procedures and IFMs must be performed to identify the fasteners with planned on-orbit use.A demonstration/evaluation of the as-built hardware (payload items) must be performed to verify that all fasteners can be actuated by one hand and this can be done by either left or right hand.

7. A review of the flight crew procedures including Malfunction Procedures and IFMs must be performed to identify the fasteners with planned on-orbit use. An inspection/evaluation or demonstration of the as-built hardware (payload items) must be performed to verify that any fasteners to be actuated on-orbit have the separation and clearances defined in SSP 52000-IDD-ERP, Figure 12-14.

8. Per IDD 3.4.3.5.1 separation interface is between payload and mounting panel. A review of the flight crew procedures including Malfunction Procedures and IFMs must be performed to identify the fasteners/tools required to remove the payload. An inspection/evaluation of the payload equipment item must be performed to verify that a minimum clearance is 0.5 in for the entire circumference of the bolt head and a minimum of 1.5 in over 180 degrees of the bolt head and provide tool handle sweep per Figure 12-14 of SSP 52000-IDD-ERP.

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Description of Verification Method: (Continued)9. An inspection/evaluation/analysis of the as-built hardware must be performed to verify that

access to payload mounting bolts has been provided.10. An inspection/evaluation analysis of the as-built hardware must be performed to verify that the

payload equipment does not require the use of special tools for payload removal, unless the special tool is provided by the PD. PDs are encouraged to use standard metric/English fasteners and tools.




L-4.5 mo









L-4.5 mo


SSP 52000-IDD-ERP: 3.4.3.5, 3.4.3.5.1B, 3.4.3.5.1C, 12.12.2, 12.12.3, 12.12.4, 12.12.6, 12.12.9A, 12.12.9B, 12.12.9C, 12.12.10, 12.12.11

Notes:

1. Exempted are NSTS standard middeck lockers or payload-provided hardware with the static envelope dimensions (cross-section) as specified in Figures 3-9, 3-10, and 3-12, and other similar captive fastener arrangements.

2. Delivery date assumes 30 days prior to turnover to KSC, and PD hardware must be turned over to KSC at L-5 months.

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Applicable Documents and Notes: (Continued)

3. Also see related VRDS HF-ER-001, “Handles, Restraints, Tether Points, and Captive Parts.”

4. “Phillips” or “torque-set” fasteners may be used where fastener installation is permanent relative to planned on-orbit operations or maintenance, or where tool-fastener interface failure can be corrected by replacement of the unit containing the affected fastener with a spare unit.

5. Also see related VRDS HF-ER-024, “Arrangement and Orientation for Connectors.”

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HF-ER-032 Latches I or D, D



1. Overcenter latches shall include a provision to prevent undesired latch element realignment, interface, or reengagement. (12.12.7A)

2. N/A

3. N/A

4. All latches, handles, and operating mechanisms shall be designed to be latched/unlatched and opened/closed with one hand by the 95th percentile American male to the 5th percentile female. (12.6.5A)

5. The design of latches shall be such that their status (locked/unlocked) can be determined through visual inspection. (12.6.5B)


1. An inspection/evaluation or demonstration of the as-built hardware (payload items) must be performed to verify that any overcenter latches include a provision to prevent undesired latch element realignment, interface, or reengagement.

2. N/A

3. N/A

4. A demonstration of the as-built hardware (latches, handles, and operating mechanisms) shall be performed to verify that it can be latched/unlatched and opened/closed with one hand by the 95th percentile American male to the 5th percentile female.

5. An inspection/evaluation of the as-built hardware (latches) shall be performed to verify that the status (locked/unlocked) can be determined visually.




L-4.5 mo


1. None Required.



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HF-ER-032 Latches I or D, D



1. None Required.



1. N/A

2. L-4.5 mo


SSP 52000-IDD-ERP: par 12.6.5A, 12.6.5B, 12.12.7A

Note: The delivery date assumes 30 days prior to turnover to KSC, and PD hardware must be turned over to KSC at L-5 months.

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HF-ER-033 Payload In-Flight Maintenance A



Payloads shall be designed to be operated and maintained using standard GFE tools defined in SSP 50449. (12.13)


A review of the flight crew procedures including Malfunction Procedures and IFMs must be performed to identify the tools required for payload on-orbit use. An analysis/evaluation of the required tools compared with the existing tools on-orbit must be performed. Any instances requiring special/unique tools must be justified.




L-4.5 mo


1. None Required.




1. None Required.



1. N/A

2. L-4.5 mo


SSP 52000-IDD-ERP: par 12.13

Notes:1. A list of available tools on-orbit are is defined at URL

http://iss-www.jsc.nasa.gov/ss/issapt/opsipt/mresup/mresup_home.html or in SSP 50449.2. Any special/unique tools must be payload provided.3. The submittal date assumes 30 days prior to turnover to KSC, and PD hardware must be

turned over to KSC at L-5 months.

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HF-ER-034 Protrusions (Permanent/Temporary) and Pathways I, A and I, D



1. Permanently attached equipment shall not protrude beyond the plane of the NASA ISPR front face GSE attachments which are 24.6 inches from the backplate of the EXPRESS Rack. (3.6.2.1)

2. On-orbit semi-permanent protrusions shall be limited to 1.3 inches beyond the plane of the NASA ISPR front face GSE attachment points (i.e., GSE plane). (3.6.2.2A)

3. All on-orbit semi-permanent protrusions shall be designed to be removable by the crew with hand operations and/or standard Intravehicular Activity (IVA) tools. (3.6.2.2B)

4. On-orbit temporary protrusions shall be limited to 17 inches beyond the GSE plane (except for payloads located in the floor or ceiling which are limited to 6 inches each or a total of 12 inches for both floor and ceiling). (3.6.2.3A)

5. N/A

6. On-orbit momentary protrusions shall be designed such that they can be eliminated within 30 sec. (3.6.2.4)

7. N/A

8. EXPRESS Rack payloads to be transferred to/from ISS laboratories, and the Orbiter shall be limited to the dimensions in SSP 52000-IDD-ERP, Sections 3.4.3 and 3.6.2 due to IVA transfer pathway limitations. Middeck payloads to be transferred to/from ISS shall be limited to 18.125 inches (width) by 21.88 inches (depth) by 21.062 inches (length) dimensions due to IVA transfer pathway limitations. (3.8)

9. On-orbit protrusions, excluding momentary protrusions, shall not extend laterally across the edges of the rack or pass between racks. (3.6.2A)

10. The payload hardware, excluding momentary protrusions, shall not prevent attachment of Rack Mobility Aid (RMA) on any seat track attach holes. Constraints which may be associated with payload protrusions include: (3.6.2B)

A. Removal of the protrusions during rack installation, translation, and crew translation.

B. Removal of the protrusions if RMA is installed on the rack.

C. Removal of the protrusions to prevent interference with microgravity operations.

D. Removal or powering off of the rack if the protrusion blocks Portable Fire Extinguisher (PFE) access or the fire indicator.

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Human Factors Verification Requirement: (Continued)

E. Limiting the payload location, e.g., protrusions located in the floor and the ceiling are limited to a total of no more than 12 inches.

As indicated by the constraints above, protrusions have a negative impact on crew operations and are to minimized.


1. An inspection/evaluation and/or analysis of the payload equipment must be performed to verify payload equipment remains within its required envelope.

2. An inspection/evaluation and/or analysis of the payload equipment must be performed to verify on-orbit semi-permanent protrusions are limited to 1.3 inches beyond the GSE plane.

3. A demonstration or analysis of the payload equipment must be performed to verify all on-orbit semi-permanent protrusions can be removed by the crew with hand operations and/or standard IVA tools.

4. An inspection/evaluation and/or analysis of the payload equipment must be performed to verify on-orbit temporary 17 inches beyond the GSE plane (except for payloads located in the floor or ceiling which are limited to 6 inches each or a total of 12 inches for both floor and ceiling.

5. A demonstration or analysis of the payload equipment must be performed to verify all on-orbit temporary protrusions can be eliminated or returned to their stowed configuration by the crew with hand operations and/or standard IVA tools within 10 minutes.

6. A demonstration or analysis of the payload equipment must be performed to verify on-orbit momentary protrusions can be eliminated within 30 seconds.

7. N/A

8. An inspection/evaluation of the as-built payload equipment items must be performed to verify that they are within the envelopes given in SSP 52000-IDD-ERP, Sections 3.4.3 and 3.6.2, and are within the envelope of 18.125 X 21.88 X 21.062 in (W x D x L).

If a payload requires a handhold for transfer operations, a clearance assessment must be included as closure for this VRDS. The clearance assessment is developed by the International Space Station Program and/or the Space Shuttle Program.

9. An inspection/evaluation and/or analysis of the payload equipment must be performed to verify payload equipment does not extend laterally across the edges of the rack or pass between racks.

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10. An inspection/evaluation and/or analysis of the payload hardware must be performed to verify payload hardware, excluding momentary protrusions, does not prevent attachment of Rack Mobility Aid (RMA) on any seat track attach holes.


1. Data Certification (Preliminary) providing drawings identifying all protrusions.

2. Data Certification (update) providing drawings identifying any new protrusions or changes to previous data certification.


L-16 mo

L-9 mo






1. Data Certification (Preliminary) providing drawings identifying all protrusions in conjunction with ICD submittal.

2. Data Certification (Update) providing drawings identifying any new protrusions or changes to previous data certification.


L-18 mo

L-11 mo


NSTS 21000-IDD-MDKSSP 30257:004SSP 50005B: par 8.8.3.1, 8.8.3.2SSP 52000-IDD-ERP: par 3.6.2A-B, 3.6.2.1, 3.6.2.2A-B, 3.6.2.3A, 3.6.2.4, 3.8

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Notes:

1. Payload protrusions of a permanent nature in the XPL-direction exceeding those defined in SSP 52000-IDD-ERP, paragraphs 3.4.3.1, 3.4.3.2, 3.4.3.3, and 3.4.3.4 shall require prior approval before inclusions into any payload-unique ICD due to difference in capabilities between the middeck and the EXPRESS Rack.

2. Payloads requiring handholds for transfer operations shall require a unique clearance assessment if they violate the maximum allowable dimensions.

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HF-ER-035 Sharp Edges/Corners Requirements I, A and I or D, A and I, A or I



1. The EXPRESS Rack payload design shall protect crewmembers from sharp edges and corners during all crew operations in accordance with NSTS 1700.7, ISS Addendum, paragraph 222.1. (3.6.3)

2. N/A

3. Threaded ends of screws and bolts accessible by the crew and extending more than 0.12 inches (3 mm) shall be covered or capped to protect against sharp threads. (3.6.3.3)

4. Exposed surfaces shall be free of burrs. (3.6.3.4)

5. Latches that pivot, retract, or flex so that a gap of less than 1.4 inches (35 mm) exists shall be designed to prevent entrapment of a crewmember’s appendage. (3.6.3.5)

6. N/A

7. N/A

8. Safety wires or lockwire shall not be used on fasteners exposed to the cabin except as required by SSP 52005, paragraph 5.6. Also see SSP 52000-IDD-ERP, paragraph 3.4.3.6.4. (3.6.3.7)

9. N/A


1. An inspection/evaluation of the payload equipment item surfaces must be performed to verify payload equipment exposed edges/surfaces meet the dimensional requirements listed above. Include areas that will be accessed during routine installation, servicing, or crew operations.

2. N/A

3. An inspection/evaluation of the payload equipment item surfaces must be performed to verify all screw/bolt ends are covered. An inspection/evaluation of the payload equipment items must be performed to verify that materials that flake or create debris if the screw/bolt has to be removed are not used.

4. An inspection/evaluation of the payload equipment item surfaces must be performed to verify all surfaces are free of burrs.

5. An analysis/evaluation of the payload equipment item latch design must be done to determine the gap for the latches to be greater than 1.4 in. An inspection/evaluation or demonstration of the as-built payload equipment item latch design must be performed to verify no entrapment potential.

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HF-ER-035 Sharp Edges/Corners Requirements I, A and I or D, A and I, A or I



An analysis/evaluation of the payload equipment must be done to identify all latches, determine if opening or closing any latch creates a gas of less than 1.4 in (35 mm), and verify through inspection/evaluation or demonstration of the as-built payload equipment that entrapment is prevented.

6. N/A

7. N/A

8. An inspection/evaluation of the as-built payload equipment items must be performed to verify no safety wire is used for fasteners exposed to the cabin.

9. N/A




L-4.5 mo


None Required.


None Required.


N/A


SSP 57000B: par 3.12.9.2SSP 52000-IDD-ERP: par 3.6.3, 3.6.3.3, 3.6.3.4, 3.6.3.5, 3.6.3.7

Notes:

1. Delivery date assumes 30 days prior to turnover to KSC, and PD hardware must be turned over to KSC at L-5 months.

2. Materials that flake or create debris if the screw/bolt has to be removed should be avoided.3. The ISIS drawer handles/latches meet the requirements of Part 5.

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HF-ER-039 Identification Labeling I or A or D



EXPRESS Rack payloads, loose equipment, stowage trays, consumables, ORUs, crew accessible connectors and cables, switches, indicators, and controls shall be labeled. Labels are markings of any form (including Inventory management System (IMS) bar codes) such as decals and placards, which can be adhered, “silk screened,” engraved, or otherwise applied directly onto the hardware. Appendix E provides instructions for label and decal design and approval. (12.5)


An inspection or analysis or demonstration of the as-built hardware shall be performed to verify EXPRESS Rack payloads, loose equipment, stowage trays, consumables, ORUs, crew accessible connectors and cables, switches, indicators, and controls are labeled.













L-4.5 mo


SSP 52000-IDD-ERP: par 12.5


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SA-ER-001 Payload Safety Requirements I


Safety Specific Verification Requirement:

Payloads shall be designed to meet the requirements in NSTS 1700.7 and ISS Addendum, 45 SPW HB S-100/KHB 1700.7, and NSTS 18798 as well as the specific safety requirements documented in this IDD. (1.2)

Description of Verification Method:Verify that the payload has developed a Safety Compliance Data Package(s) in accordance with NSTS 13830 and that the applicable safety requirements of NSTS 1700.7, ISS Addendum, KHB 1700.7, and SSP 52000-IDD-ERP have been adequately addressed.


Copy of the Safety Compliance Data Package submitted to Engineering Integration (EI) at the time package is delivered to the Safety Panel for scheduled payload flight and ground safety reviews.


L-10 moFlight Safety Review (Phase II and Phase

III) -45 days


Verify that the payload has developed a Safety Compliance Data Package(s) in accordance with NSTS 13830 and that the applicable safety requirements of NSTS 1700.7, ISS Addendum, KHB 1700.7, and SSP 52000-IDD-ERP have been adequately addressed.


Copy of the Safety Compliance Data Package submitted to Engineering Integration (EI) at the time package is delivered to the Safety Panel for scheduled payload flight and ground safety reviews.

Data Submittal Dates:45 days prior to

applicable safety reviews for reflight

payloads.


KHB 1700.7: total documentNSTS 13830NSTS 1700.7: total document NSTS 1700.7, ISS Addendum: total documentSSP 52000-IDD-ERP: par 1.2

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APPENDIX C

ABBREVIATIONS AND ACRONYMS

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C-ii

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APPENDIX C, ABBREVIATIONS AND ACRONYMS

A ampAAA Avionics Air Assemblyac alternating currentADVASC Advanced AstrocultureANSI American National Standards InstitutionAPM Attached Pressurized ModuleARIS Active Rack Isolation SystemAWG American Wire Gauge

Btu British Thermal Unit

C CelsiusC&DH Command and Data HandlingCAM Centrifuge Accommodation ModuleCB Change BoardCc cubic centimetersCCB Change Control BoardCG Center of Gravitycm centimeterCM Crew ModuleCMG Control Moment GyroscopeCOC Certificate of ComplianceCoFR Certificate of Flight ReadinessCOU Concepts of UtilizationCPCG-H Commercial Protein Crystal Growth – High Density Protein Crystal GrowthCSCI Computer Software Configuration Item

dBpT decibel picotesladc direct currentDCB Development Control BoardDFRC Dryden Flight Research CenterDRR Document Release Record

ECW Emergency, Caution, WarningEI Engineering IntegrationEIA EXPRESS Integration AgreementEMC Electromagnetic CompatibilityEMI Electromagnetic Interference

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EMU EXPRESS Memory UnitEPIM EXPRESS Payload Integration ManagerER EXPRESS RackERO EXPRESS Rack OfficeERP EXPRESS Rack PayloadESA European Space AgencyESD Electrostatic DischargeETR EXPRESS Transportation RackEUT Equipment Under TestEXPRESS EXpedite the PRocessing of Experiments to Space Station

F FahrenheitFCP Fracture Control PlanFED FederalFt foot

GFE Government Furnished EquipmentGFP Government Furnished PropertyGN2 Gaseous NitrogenGPVP Generic Payload Verification PlanGSE Ground Support Equipment

H&S Health and StatusHDBK Handbookhr hourHz Hertz

ICD Interface Control DocumentID IdentifierIDD Interface Definition DocumentIEEE Institution of Electrical and Electronic EngineersIMS Inventory Management SystemIRD Interface Requirements DocumentISIS International Subrack Interface StandardISPR International Standard Payload RackISS International Space StationISSP International Space Station ProgramIVA Intravehicular Activity

JEM Japanese Experiment ModuleJMICB Joint Mission Integration Control Board

C-2

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JPRCB Joint Program Review Control BoardJSC Johnson Space Center

Kg kilogramKHB Kennedy HandbookKHZ kilohertzKSC Kennedy Space Center

lb poundlbm pound massLISN Line Impedance Simulation Network

M meterM&P Materials and Processesmax maximumMDK MiddeckMDL Middeck LockerMDLE Middeck Locker EquivalentMDP Maximum Design PressureMHz MegahertzMIL Militarymin minimumMPICB Multilateral Payload Interface Control BoardMPLM Multi-Purpose Logistics ModuleMSFC Marshall Space Flight CenterMTL Moderate Temperature LoopMUA Materials Usage AgreementMUPG Multi-Use Payload Group

N/A Not ApplicableNAR Not a RequirementNASA National Aeronautics and Space AdministrationNSTS National Space Transportation System

ODS Orbiter Docking SystemORU Orbital Replacement Unit

PAH Payload Accommodations HandbookPARD Periodic and Random DeviationPAS Payload Application SoftwarePCB Payload Control Board

C-3

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PCG-STES Protein Crystal Growth-Single-Locker Thermal Enclosure SystemPCS Portable Computer SystemPD Payload DeveloperPDL Payload Data LibraryPDR Payload Design ReviewPEHB Payload Ethernet Hub BridgePEI Payload Engineering IntegrationPEP Payload Executive ProcessorPFE Portable Fire ExtinguisherPGSC Payload and General Support ComputerPIRN Preliminary/Proposed Interface Revision NoticePL PayloadPL MDM Payload Multiplexer/DemultiplexerPMP Payload mounting PanelPODF Payload operations Data FilePPCB Point-to-Point Communication BusPRV Pressure Relief ValvePSRP Payload Safety Review PanelpT picoTeslaPTR Payload Technical ReviewPU Payload UnitPVP Payload Verification PlanPVPP Payload Verification Program Plan

QD Quick Disconnect

RF Radio FrequencyRIC Rack Interface ControllerRMA Rack Mobility Aid

SCC Stress Corrosion CrackingSCS Safety Critical StructuresScS Suitcase SimulatorSEE Single Event EffectSHR Safety Hazard ReportSPEC SpecificationSPL Sound Pressure LevelsSSP Space Station ProgramSSPC Solid State Power ControllerSSPCM Solid State Power Controller ModuleSTD Standard

C-4

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SVP Structure Verification PlanSWG Structures Working Group

TBD To Be DeterminedTBE Teledyne Brown EngineeringTCP/IP Transmission Control Protocol/Internet ProtocolTES Thermal Enclosure SystemTM Technical Memorandum

UF Utilization FlightUSL United States Laboratory

V VoltVCL Verification Coupled LoadsVC-S Visibly Clean-SensitiveVDACS Video and Data Acquisition and Control SystemVdc Volts, direct currentVES Vacuum Exhaust SystemVPMP Vented Payload Mounting PanelVRDS Verification Requirement Definition SheetVTR Video Tape Recorder

W WattWCCS Wireless Crew Communication SystemWCSAR Wisconsin Center for Space Automation and Robotics

C-5

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C-6

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