> **LANDSAT DATA CONTINUITY**
>
> **MISSION**
>
> **OPERATIONAL LAND IMAGER**
>
> **(OLI)**
>
> **MISSION ASSURANCE REQUIREMENTS**
>
> **April 19, 2005**

![](media/image1.png)

**Signature Page**

+----------------------------------+-----------------------------------+
| ***Prepared by:***               |                                   |
+----------------------------------+-----------------------------------+
| \_\_\_\_\_\_\_                   |                                   |
|                                  |                                   |
| Jack Ellis Date                  |                                   |
|                                  |                                   |
| LDCM Systems Assurance Manager   |                                   |
|                                  |                                   |
| GSFC -- Code 303                 |                                   |
+----------------------------------+-----------------------------------+
| ***Reviewed by:***               |                                   |
+----------------------------------+-----------------------------------+
| \_\_\_\_\_\_\_                   |                                   |
|                                  |                                   |
| Jeanine Murphy-Morris Date       |                                   |
|                                  |                                   |
| OLI Instrument Manager           |                                   |
|                                  |                                   |
| GSFC -- Code 427                 |                                   |
+----------------------------------+-----------------------------------+
| ***Approved by:***               |                                   |
+----------------------------------+-----------------------------------+
| \_\_\_\_\_\_\_\_                 |                                   |
|                                  |                                   |
| William Ochs Date Date           |                                   |
|                                  |                                   |
| LDCM Project Manager             |                                   |
|                                  |                                   |
| GSFC -- Code 427                 |                                   |
+----------------------------------+-----------------------------------+

![](media/image2.pct){width="1.0416666666666666e-2in"
height="1.0416666666666666e-2in"}**LDCM PROJECT**

**DOCUMENT CHANGE RECORD**

Sheet: 1 of 1

+------------+--------------------------------------------+-----------+
| REV        | DESCRIPTION OF CHANGE                      | DATE      |
|            |                                            |           |
| LEVEL      |                                            | APPROVED  |
+------------+--------------------------------------------+-----------+
|            |                                            |           |
+------------+--------------------------------------------+-----------+

**TABLE OF CONTENTS**

Page

[1.0 OVERALL REQUIREMENTS 1-1](#overall-requirements)

[1.1 GENERAL REQUIREMENTS 1-1](#general-requirements)

[1.2 USE OF MULTI-MISSION OR PREVIOUSLY DESIGNED, FABRICATED, OR FLOWN
HARDWARE
1-1](#use-of-multi-mission-or-previously-designed-fabricated-or-flown-hardware)

[1.3 SURVEILLANCE OF THE CONTRACTOR
1-1](#surveillance-of-the-contractor)

[1.4 REFERENCE DOCUMENTS 1-2](#reference-documents)

[1.5 ACRONYMS AND GLOSSARY 1-2](#acronyms-and-glossary)

[Definitions and acronyms are listed in the OLI Acronym List and
Lexicon.
1-2](#definitions-and-acronyms-are-listed-in-the-oli-acronym-list-and-lexicon.)

[2.0 QUALITY ASSURANCE REQUIREMENTS
2-1](#quality-assurance-requirements)

[2.1 GENERAL REQUIREMENTS 2-1](#general-requirements-1)

[2.2 SUPPLEMENTAL QMS REQUIREMENTS 2-1](#supplemental-qms-requirements)

[2.2.1 Control of Nonconforming Product
2-1](#control-of-nonconforming-product)

[2.2.2 Control of Monitoring and Measuring Devices
2-2](#control-of-monitoring-and-measuring-devices)

[2.2.3 Configuration Management 2-2](#configuration-management)

[2.2.4 Requirements Flow-Down 2-2](#requirements-flow-down)

[2.2.5 Ground Support Equipment (GSE)
2-3](#ground-support-equipment-gse)

[2.2.6 Manufacturing, Assembly, and Test Documentation
2-3](#manufacturing-assembly-and-test-documentation)

[2.3 HANDLING, STORAGE, PRESERVATION, MARKING, LABELING, PACKAGING,
PACKING, AND SHIPPING
2-3](#handling-storage-preservation-marking-labeling-packaging-packing-and-shipping)

[2.4 GOVERNMENT ACCEPTANCE 2-3](#government-acceptance)

[3.0 SYSTEM SAFETY REQUIREMENTS 3-1](#system-safety-requirements)

[3.1 GENERAL REQUIREMENTS 3-1](#general-requirements-2)

[3.2 SYSTEM SAFETY PROGRAM PLAN (SSPP)
3-1](#system-safety-program-plan-sspp)

[3.3 MISSILE SYSTEM PRELAUNCH SAFETY PLAN (MSPSP) INPUTS
3-1](#missile-system-prelaunch-safety-plan-mspsp-inputs)

[3.4 GROUND OPERATIONS PROCEDURES 3-2](#ground-operations-procedures)

[3.5 SAFETY NONCOMPLIANCE REQUESTS 3-2](#safety-noncompliance-requests)

[3.6 SUPPORT FOR SAFETY WORKING GROUP MEETINGS
3-2](#support-for-safety-working-group-meetings)

[3.7 ORBITAL DEBRIS ASSESSMENT 3-2](#orbital-debris-assessment)

[3.8 SOFTWARE SAFETY 3-2](#software-safety)

[4.0 RELIABILITY REQUIREMENTS 4-1](#reliability-requirements)

[4.1 GENERAL REQUIREMENTS 4-1](#general-requirements-3)

[4.2 RELIABILITY PLAN 4-1](#reliability-plan)

[4.3 PROBABILISTIC RISK ASSESSMENT 4-1](#probabilistic-risk-assessment)

[4.4 RELIABILITY ANALYSES 4-2](#reliability-analyses)

[4.4.1 Failure Modes and Effects Analysis and Critical Items List
4-2](#failure-modes-and-effects-analysis-and-critical-items-list)

[4.4.2 Fault Tree Analysis 4-3](#fault-tree-analysis)

[4.4.3 Parts Stress Analyses 4-4](#parts-stress-analyses)

[4.4.4 Worst-Case Analyses 4-4](#worst-case-analyses)

[4.4.5 Software Reliability 4-4](#software-reliability)

[4.4.6 Reliability Block Diagram 4-5](#reliability-block-diagram)

[4.5 RELIABILITY ANALYSIS OF TEST DATA
4-5](#reliability-analysis-of-test-data)

[4.5.1 Trend Analyses 4-5](#trend-analyses)

[4.6 LIMITED-LIFE ITEMS 4-5](#limited-life-items)

[4.7 CONTROL OF SUBCONTRACTORS AND SUPPLIERS
4-6](#control-of-subcontractors-and-suppliers)

[5.0 SOFTWARE ASSURANCE REQUIREMENTS
5-1](#software-assurance-requirements)

[5.1 GENERAL REQUIREMENTS 5-1](#general-requirements-4)

[5.2 SOFTWARE TECHNICAL REVIEWS 5-1](#software-technical-reviews)

[5.3 SOFTWARE QUALITY ASSURANCE (SQA)
5-2](#software-quality-assurance-sqa)

[5.4 SOFTWARE VERIFICATION AND VALIDATION
5-2](#software-verification-and-validation)

[5.5 SAFETY ASSURANCE 5-2](#safety-assurance)

[5.6 GFE, EXISTING AND PURCHASED SOFTWARE/FIRMWARE (SW/FW)
5-3](#gfe-existing-and-purchased-softwarefirmware-swfw)

[6.0 PARTS REQUIREMENTS 6-1](#parts-requirements)

[6.1 GENERAL REQUIREMENTS 6-1](#general-requirements-5)

[6.2 ELECTRICAL, ELECTRONIC, AND ELECTROMECHANICAl (EEE) parts
6-1](#electrical-electronic-and-electromechanical-eee-parts)

[6.2.1 Quality Level 6-1](#quality-level)

[6.2.2 Parts Control Board 6-1](#parts-control-board)

[6.2.3 Parts Selection and Processing
6-2](#parts-selection-and-processing)

[6.2.4 De-rating 6-2](#de-rating)

[6.2.5 Radiation Hardness 6-2](#radiation-hardness)

[6.2.6 Verification Testing 6-3](#verification-testing)

[6.2.7 Destructive Physical Analysis (DPA)
6-3](#destructive-physical-analysis-dpa)

[6.2.8 Failure Analysis 6-3](#failure-analysis)

[6.2.9 Parts Age Control 6-3](#parts-age-control)

[6.3 PARTS LIST 6-4](#parts-list)

[6.3.1 Project Approved Parts List 6-4](#project-approved-parts-list)

[6.3.2 Parts Identification List 6-4](#parts-identification-list)

[6.3.3 As-Built Parts List 6-4](#as-built-parts-list)

[6.3.4 Parts List Information 6-4](#parts-list-information)

[6.4 GIDEP ALERTS AND PROBLEM ADVISORIES
6-5](#gidep-alerts-and-problem-advisories)

[7.0 MATERIALS, PROCESSES, AND LUBRICATION REQUIREMENTS
7-1](#materials-processes-and-lubrication-requirements)

[7.1 GENERAL REQUIREMENTS 7-1](#general-requirements-6)

[7.2 MATERIALS SELECTION REQUIREMENTS
7-1](#materials-selection-requirements)

[7.2.1 Material Identification List (MIL)
7-1](#material-identification-list-mil)

[7.2.2 Compliant Materials 7-1](#compliant-materials)

[7.2.3 Non-compliant Materials 7-2](#non-compliant-materials)

[7.2.4 Conventional Applications 7-2](#conventional-applications)

[7.2.5 Non-conventional Applications
7-2](#non-conventional-applications)

[7.2.6 Polymeric Materials 7-3](#polymeric-materials)

[7.2.7 Inorganic Materials 7-3](#inorganic-materials)

[7.2.8 Lubrication 7-4](#lubrication)

[7.3 PROCESS SELECTION REQUIREMENTS
7-4](#process-selection-requirements)

[7.4 PROCUREMENT REQUIREMENTS 7-4](#procurement-requirements)

[7.4.1 Purchased Raw Materials 7-4](#purchased-raw-materials)

[7.4.2 Raw Materials Used in Purchased Products
7-5](#raw-materials-used-in-purchased-products)

[8.0 RESERVED 8-1](#reserved)

[9.0 DESIGN VERIFICATION REQUIREMENTS
9-1](#design-verification-requirements)

[9.1 GENERAL REQUIREMENTS 9-1](#general-requirements-7)

[9.2 DOCUMENTATION REQUIREMENTS 9-1](#documentation-requirements)

[9.2.1 System Performance Verification Plan
9-1](#system-performance-verification-plan)

[9.2.2 Environmental Verification Plan
9-2](#environmental-verification-plan)

[9.3 ELECTRICAL FUNCTIONAL TEST REQUIREMENTS
9-4](#electrical-functional-test-requirements)

[9.3.1 Electrical Interface Tests 9-4](#electrical-interface-tests)

[9.3.2 Aliveness Tests 9-4](#aliveness-tests)

[9.3.3 Comprehensive Performance Tests (CPTs)
9-4](#comprehensive-performance-tests-cpts)

[9.3.4 Limited Performance Tests (LPTs)
9-4](#limited-performance-tests-lpts)

[9.3.5 Support to End-to-End Performance Tests
9-5](#support-to-end-to-end-performance-tests)

[9.3.6 Performance Operating Time and Failure-Free Performance Testing
9-5](#performance-operating-time-and-failure-free-performance-testing)

[9.4 Environmental Testing REQUIREMENTS
9-5](#environmental-testing-requirements)

[10.0 WORKMANSHIP STANDARDS 10-1](#workmanship-standards)

[10.1 GENERAL REQUIREMENTS 10-1](#general-requirements-8)

[10.2 APPLICABLE DOCUMENTS 10-1](#applicable-documents)

[10.3 DESIGN 10-2](#design)

[10.3.1 Printed Wiring Boards (PWB) 10-2](#printed-wiring-boards-pwb)

[10.3.2 Ground Data Systems (GDS) 10-2](#ground-data-systems-gds)

[10.4 WORKMANSHIP REQUIREMENTS 10-2](#workmanship-requirements)

[10.4.1 Training and Certification 10-2](#training-and-certification)

[10.4.2 Flight Workmanship 10-2](#flight-workmanship)

[10.4.3 GDS (non-flight) Workmanship 10-3](#gds-non-flight-workmanship)

[10.5 ESD REQUIREMENTS 10-3](#esd-requirements)

[10.6 NEW/ADVANCED PACKAGING TECHNOLOGIES
10-3](#newadvanced-packaging-technologies)

[11.0 RISK MANAGEMENT REQUIREMENTS 11-1](#risk-management-requirements)

[11.1 GENERAL REQUIREMENTS 11-1](#general-requirements-9)

[11.2 RISK MANAGEMENT PLAN 11-1](#risk-management-plan)

[12.0 CONTAMINATION CONTROL REQUIREMENTS
12-1](#contamination-control-requirements)

[12.1 GENERAL REQUIREMENTS 12-1](#general-requirements-10)

[12.2 CONTAMINATION CONTROL PLAN 12-2](#contamination-control-plan)

[12.3 MATERIAL OUTGASSING 12-2](#material-outgassing)

[12.4 THERMAL VACUUM BAKEOUT 12-2](#thermal-vacuum-bakeout)

[Appendix A REFERENCE DOCUMENTS LIST 1](#__RefHeading___Toc100548489)

**LIST OF FIGURES**

[Figure]{.underline} [Page]{.underline}

[Figure 7‑1. MUA 7-6](#__RefHeading___Toc75054500)

[Figure 7‑2. Stress Corrosion Evaluation Form
7-7](#__RefHeading___Toc75054501)

[Figure 7‑3. Polymeric Materials and Composites Usage List
7-8](#__RefHeading___Toc75054502)

[Figure 7‑4. Inorganic Materials and Composites Usage List
7-9](#__RefHeading___Toc75054503)

[Figure 7‑5. Lubrication Usage List 7-10](#__RefHeading___Toc75054504)

[Figure 7‑6. Materials Process Utilization List
7-11](#__RefHeading___Toc75054505)

**LIST OF TABLES**

[Table]{.underline} [Page]{.underline}

[Table 4‑1. Severity Categories 4-3](#__RefHeading___Toc75054521)

[Table 7‑1. Material Selection Criteria
7-2](#__RefHeading___Toc75054522)

# OVERALL REQUIREMENTS

## GENERAL REQUIREMENTS

This document presents the Goddard Space Flight Center (GSFC) LDCM
Operational Land Imager (OLI) Safety and Mission Assurance (SMA)
requirements. The Contractor shall have an organized SMA program for
flight hardware/software and ground support equipment as defined in this
document appropriate to the nature of the particular hardware or
software to be delivered. The SMA program shall encompass all software
critical for mission success and the ground system that interfaces with
flight equipment to the extent necessary to ensure the integrity and
safety of flight items.

Managers of the assurance activities shall have direct access to
Contractor management independent of project management, with the
functional freedom and authority to interact with all other elements of
the project.

A Quality Manual that provides for control and traceability through all
phases of the design, manufacturing, and testing of deliverable items
shall be made available for review. If needed, supplemental plans or
procedures describing how the requirements of this document will be
accomplished shall be developed and made available for project review.
The rationale for any planned noncompliance with a requirement shall be
submitted to the GSFC LDCM Project for approval. In this document, the
term "LDCM Project approval" means the approval of Government
Contracting Officer (CO) or the Contracting Officer's Technical Officer
(COTR).

## USE OF MULTI-MISSION OR PREVIOUSLY DESIGNED, FABRICATED, OR FLOWN HARDWARE

When hardware that was designed, fabricated, or flown on a previous
project is considered to have demonstrated compliance with some or all
of the requirements of this document, such that certain tasks need not
be repeated, the Contractor shall demonstrate how the hardware complies
with LDCM requirements.

## SURVEILLANCE OF THE CONTRACTOR

The work activities, operations, and documentation performed by the
Contractor or his suppliers are subject to evaluation, review, audit,
and inspection by government-designated representatives from the GSFC
LDCM Project, the Government Inspection Agency (GIA), or an independent
assurance contractor (IAC). In-plant responsibilities and authority to
those agencies will be documented via a letter of delegation or contract
with the IAC. The quality assurance (QA) representatives shall be
provided documents, records, and equipment needed to perform their
assurance and safety related surveillance activities, including a
suitable in-plant work area (upon request).

## REFERENCE DOCUMENTS

To the extent referenced herein, applicable portions of the documents
listed in Appendix A form a part of this document.

## ACRONYMS AND GLOSSARY

# Definitions and acronyms are listed in the OLI Acronym List and Lexicon.  {#definitions-and-acronyms-are-listed-in-the-oli-acronym-list-and-lexicon. .unnumbered}

# QUALITY ASSURANCE REQUIREMENTS

## GENERAL REQUIREMENTS

A Quality Management System (QMS) that is compliant with the minimum
requirements of ANSI/ISO/ASQ Q9001-2000 (or equivalent) shall be
planned, documented, and implemented. International Organization for
Standardization (ISO) certification is not mandatory. The Contractor
Quality Manual shall be made available for the GSFC LDCM Project review
at the Contractor\'s facility.

## SUPPLEMENTAL QMS REQUIREMENTS

Assurance related requirements not adequately covered by ANSI/ISO/ASQ
Q9001-2000 are identified in the following sections.

### Control of Nonconforming Product

Nonconforming Product is a condition of any hardware, software,
material, or service in which one or more characteristics do not conform
to requirements. Nonconforming products fall into two
categories\--discrepancies and failures.

a.  A discrepancy is a departure from specification that is detected
    during inspection or process control testing, etc., while the
    hardware or software is not functioning or operating (typically
    addressed via Material Review Board (MRB) process).

b.  A failure is a departure from specification that is discovered in
    the functioning or operation of the hardware or software (typically
    addressed via Failure Review Board (FRB) process).

#### Nonconformance Reporting and Corrective Action (NRCA)

The Contractor shall have a system for:

a.  Identifying and reporting nonconforming hardware and software
    through a closed loop reporting system

```{=html}
<!-- -->
```
c.  Controlling and segregating nonconforming material from normal
    production flow

d.  Ensuring that positive corrective action is implemented to preclude
    recurrence

e.  Verifying the adequacy of implemented corrective action by audit and
    test, as appropriate

##### Reporting of Discrepancies

A system for documenting and tracking the disposition of all
discrepancies shall be implemented. The GSFC LDCM Project shall be
provided access to Contractor's material discrepancy data files
applicable to LDCM.

##### Reporting of Failures

An electronic database system for documenting and tracking the
disposition of all failures shall be implemented. The GSFC LDCM Project
shall be provided access to Contractor's failure data files applicable
to LDCM and FRB meeting schedules and agenda. Failure reporting shall
begin with the first "power on application" tests at the component level
or the first operation of a mechanical item.

Failure reports shall be submitted to the GSFC LDCM Project office for
review. Failures shall be reported verbally within 24 hours of
occurrence. Written reports documenting the failure shall be provided
within 3 business days. The Contractor shall submit a list of all open
failure reports and a separate list of the failure reports closed during
the month.

### Control of Monitoring and Measuring Devices

Testing and Calibration Laboratories shall be compliant with the
requirements of ANSI/ISO 17025 -- General Requirements for the
Competence of Testing and Calibration Laboratories.

### Configuration Management

The Contractor shall prepare and use a CM System that provides control
of changes to hardware, software products and documentation. The CM
system shall provide baseline control, configuration identification,
configuration control, configuration status accounting, and
configuration authentication through reports to and audits by the LDCM
Project CMO.

Control of changes to software products shall begin in the testing phase
and continue until delivery. Formal Software CM (SCM) control shall be
implemented in the development cycle no later than first use with flight
hardware. A SCM baseline shall be established after each formal software
build.

Any flight or GSE item that is found to be non-compliant with the
requirements of the contract SOW or this MAR and is not reworked to be
compliant, or is not replaced with a compliant item, shall be presented
for disposition via a waiver. Waivers will typically affect mission
requirements, system safety, cost, schedule, risk or external
interfaces. Waivers shall be submitted to the GSFC LDCM Project office
for final approval.

### Requirements Flow-Down

The Contractor shall ensure flow-down of this MAR and system technical
requirements to all suppliers and establish a process to verify
compliance. The contract review and purchasing processes shall indicate
the process for documenting, communicating, and reviewing requirements
with sub-tier suppliers to ensure requirements are met.

### Ground Support Equipment (GSE)

The Contractor shall address safety and mission assurance for GSE.
Mechanical and electrical GSE and associated software that directly
interfaces with flight deliverable items shall be assembled and
maintained to the same standards as the deliverable flight items
(reference Sections 10.3.2 and 10.4.3).

### Manufacturing, Assembly, and Test Documentation

A traveler system shall be established to plan and document all
manufacturing, assembly, and test activities. Traveler steps may
reference controlled procedures, processes and associated drawings.

##  HANDLING, STORAGE, PRESERVATION, MARKING, LABELING, PACKAGING, PACKING, AND SHIPPING

The Contractor shall prepare and implement procedures for the handling,
storage, preservation, marking, labeling, packaging, packing, and
shipping of all products. Procedures shall be submitted in accordance
with the CDRL.

## GOVERNMENT ACCEPTANCE

Prior to acceptance by the Government, quality assurance personnel shall
ensure that deliverable contract end-items, including the Acceptance
Data Package and Software Delivery Package, are in accordance with
contract requirements. A copy of the data package shall be submitted to
the Government in accordance with the CDRL.

# SYSTEM SAFETY REQUIREMENTS

## GENERAL REQUIREMENTS

The Contractor's system safety program shall be initiated in the concept
phase of design and continue throughout all phases of the mission. GSFC
Safety Office will certify safety compliance prior to the Pre-Ship
Review. The Contractor's system safety program shall accomplish the
following:

a.  Provides for the early identification and control of hazards to
    personnel, facilities, support equipment, and the flight system
    during all stages of project development including design,
    fabrication, test, transportation and ground activities. The program
    shall address hazards in the flight hardware, associated software,
    ground support equipment, operations, and support facilities, and
    shall conform to the safety review process requirements of
    NASA-STD-8719.8, "Expendable Launch Vehicle Payloads Safety Review
    Process Standard".

```{=html}
<!-- -->
```
f.  Meets the system safety requirements of AFSPC MAN 91-710 "Range
    Safety User Requirements Manual" and KHB 1710.2, \"Kennedy Space
    Center Safety Practices Handbook\".

g.  Meets the baseline industrial safety requirements of the
    institution, AFSPC MAN 91-710, applicable Industry Standards to the
    extent practical to meet NASA and OSHA design and operational needs,
    and any special contractually imposed mission unique obligations.
    This should be documented in the contractor\'s Facility Health and
    Safety Plan.

## SYSTEM SAFETY PROGRAM PLAN (SSPP)

The Contractor shall prepare a System Safety Program Plan (SSPP) that
describes in detail, tasks and activities of system safety management
and system safety engineering required to identify, evaluate, eliminate,
and control hazards, or reduce the associated risk to a level acceptable
throughout the system life cycle. The plan provides a formal basis of
understanding between the Contractor and GSFC on how the system safety
program will be conducted to meet the requirements of AFSPC 91-710 and
NPR 8715.3, including general and specific provisions. The plan shall
account for all contractually required tasks and responsibilities on an
item-by-item basis and will address roles and responsibilities. The plan
should be made available for the Government to review.

## MISSILE SYSTEM PRELAUNCH SAFETY PLAN (MSPSP) INPUTS 

The Contractor shall perform a safety assessment and hazard analysis of
the instrument. This safety assessment, which is an input to the Missile
System Prelaunch Safety Package, shall identify all safety features of
the hardware, software, and system design, as well as procedural related
hazards present in the system. It shall include:

a.  Safety criteria and methodology used to classify and rank hazards

```{=html}
<!-- -->
```
h.  Results of hazard analyses and tests used to identify hazards in the
    system

i.  Hazard reports documenting the results of the safety program efforts

j.  List of hazardous materials generated or used in the system

k.  Conclusion with a signed statement that all identified hazards have
    been eliminated or controlled to an acceptable level

l.  Recommendations applicable to hazards at the interface of their
    system

m.  List of safety non-compliances and associated rationale for
    acceptance

## GROUND OPERATIONS PROCEDURES

All ground operations procedures to be used at GSFC facilities, other
integration facilities, or the launch site shall be submitted to the
GSFC LDCM Project Office. All hazardous instrument operations as well as
the procedures to control them shall be identified and highlighted. All
launch site procedures shall comply with the launch site and NASA safety
regulations.

## SAFETY NONCOMPLIANCE REQUESTS

When a specific safety requirement cannot be met, an associated safety
noncompliance request shall be submitted to the GSFC LDCM Project Office
that identifies the hazard and shows the rationale for approval of a
noncompliance, as defined in the requirements of AFSPC 91-710.

## SUPPORT FOR SAFETY WORKING GROUP MEETINGS

The Contractor shall provide technical support to the Project for safety
working group meetings, Technical Interface Meetings (TIM), and
technical reviews.

## ORBITAL DEBRIS ASSESSMENT

The Contractor shall provide information required to produce the
assessment consistent with NPD 8710.3, Policy for Limiting Orbital
Debris Generation and NSS 1740.14, Guidelines and Assessment Procedures
for Limiting Orbital Debris to the LDCM Project.

## SOFTWARE SAFETY

The Contractor shall establish a software safety program to identify and
mitigate safety-critical software products. If any software component is
identified as safety-critical, the Contractor shall conduct a software
safety program on that component in compliance with NASA-STD-8719.13A,
"NASA Software Safety Standard\".

The software safety program shall ensure that:

a.  Safety-related deficiencies in specifications and design are
    identified and corrected

```{=html}
<!-- -->
```
n.  Software design incorporates positive measures to enhance the safety
    of the system

o.  Software safety is included as an agenda item for formal reviews

The software safety process shall include the following activities:

a.  Determination of the safety criticality for each software component

```{=html}
<!-- -->
```
p.  Analysis of the consistency, completeness, correctness, and
    testability of safety requirements

q.  Analysis of design and code as required to ensure implementation of
    safety-critical requirements

r.  Analysis of changes for safety impact

# RELIABILITY REQUIREMENTS

## GENERAL REQUIREMENTS

The Contractor shall develop and implement a reliability program
applicable to the development of all software and hardware products and
processes. The reliability program shall:

a.  Demonstrate that redundant functions, including alternative paths
    and work-arounds, are independent to the extent practicable.

```{=html}
<!-- -->
```
s.  Demonstrate that the stress applied to parts is not excessive.

t.  Identify single failure items/points, their effect on the attainment
    of mission objectives, and possible safety degradation.

u.  Show that the reliability design aligns with mission design life and
    is consistent among the systems, subsystems, and components.

v.  Identify limited-life items and ensure that special precautions are
    taken to conserve their useful life for on-orbit operations.

w.  Select significant engineering parameters for the performance of
    trend analysis to identify performance trends during pre-launch
    activities.

x.  Ensure that the design permits easy replacement of parts and
    components and that redundant paths are easily monitored.

## RELIABILITY PLAN

The Contractor shall develop, implement, and maintain a Reliability
Program Plan. The plan shall address the approach for the reliability
activities and associated risk management functions, identify the
reliability tasks to be performed, describe how reliability assessments
will be integrated with the design, and discuss the scheduling of these
tasks relative to the LDCM Project milestones.

The Reliability Program Plan shall be made available at the
Contractor\'s facility for the LDCM Project review.

## PROBABILISTIC RISK ASSESSMENT

The Contractor shall provide the information necessary for the
Government to perform comparative numerical reliability assessments
and/or predictions to:

a.  Evaluate alternative design concepts, redundancy and cross-strapping
    approaches, and part substitutions

b.  Identify the elements of the design which are the greatest
    detractors of system reliability

c.  Identify those potential mission limiting elements and components
    that will require special attention in part selection, testing,
    environmental isolation, and/or special operations

d.  Assist in evaluating the ability of the design to achieve the
    mission life requirement and other reliability goals and
    requirements as applicable

e.  Evaluate the impact of proposed engineering change and waiver
    requests on reliability

## RELIABILITY ANALYSES

The Contractor shall perform reliability analyses concurrently with the
design so that identified problem areas can be addressed and corrective
action taken (if required) in a timely manner.

### Failure Modes and Effects Analysis and Critical Items List

The Contractor shall perform a Failure Modes and Effects Analysis (FMEA)
early in the design phase to identify system design problems and
associated critical items list (CIL). As additional design information
becomes available, the FMEA shall be refined.

Failure modes shall be assessed at the component interface level. Each
failure mode shall be assessed for the effect at that level of analysis,
the next higher level, and upward. The failure mode shall be assigned a
severity category based on the most severe effect caused by a failure.

Mission phases (launch, deployment, on-orbit operation) shall be
addressed in the analysis.

Severity categories shall be determined in accordance with Table 4-1:

FMEA analysis procedures and documentation shall be performed in
accordance with documented procedures. Failure modes resulting in
Severity Categories 1, 1R, 1S or 2 shall be analyzed at a greater depth,
to the single parts if necessary, to identify the cause of failure.

Results of the FMEA shall be used to evaluate the design relative to
requirements (e.g., no single subsystem failure will prevent removal of
power from the subsystem). Identified discrepancies shall be evaluated
by management and design groups for assessment of the need for
corrective action.

The FMEA shall analyze redundancies to ensure that redundant paths are
isolated or protected such that any single failure that causes the loss
of a functional path will not affect the other functional path(s) or the
capability to switch operation to that redundant path.

[]{#__RefHeading___Toc75054521 .anchor}Table 4‑1. Severity Categories

  ----------- -------------- ---------------------------------------------
  Category    Severity       Description

  1           Catastrophic   Failure modes that could result in serious
                             injury, loss of life (flight or ground
                             personnel), or loss of launch vehicle.

  1R                         Failure modes of identical or equivalent
                             redundant hardware items that could result in
                             category 1 effects if all failed.

  1S                         Failure in a safety or hazard monitoring
                             system that could cause the system to fail to
                             detect a hazardous condition or fail to
                             operate during such condition and lead to
                             Severity Category 1 consequences.

  2           Critical       Failure modes that could result in loss of
                             one or more mission objectives as defined by
                             the GSFC project office.

  2R                         Failure modes of identical or equivalent
                             redundant hardware items that could result in
                             Category 2 effects if all failed.

  3           Significant    Failure modes that could cause degradation to
                             mission objectives.

  4           Minor          Failure modes that could result in
                             insignificant or no loss to mission
                             objectives.
  ----------- -------------- ---------------------------------------------

All failure modes that are assigned to Severity Categories 1, 1R, 1S,
and 2, shall be itemized on a Critical Items List (CIL) and maintained
with the FMEA report. Rationale for retaining the items shall be
included on the CIL. The FMEA and CIL shall be maintained at the
Contractor's facility for GSFC LDCM Project review and/or audit. Results
of the FMEA and the CIL shall be presented at all design reviews
starting with the PDR. The presentations shall include comments on how
the analysis was used to perform design trade-offs or how the results
were taken into consideration when making design or risk management
decisions.

### Fault Tree Analysis

The Contractor shall perform Fault Tree Analyses (FTAs) that address
both mission failures and degraded modes of operation. FTAs shall be
retained for LDCM Project review upon request. Beginning with each
undesired state (mission failure or degraded mission), the fault tree
shall be expanded to include all credible combinations of events/faults
and environments that could lead to that undesired state. Component
hardware/software failures, external hardware/software failures, and
human factors shall be considered in the analysis. The fault tree itself
is not a quantitative model, but becomes a quantitative assessment when
combined with quantitative data as part of the PRA.

### Parts Stress Analyses

The Contractor shall perform stress analyses on Electrical, Electronic,
and Electromechanical (EEE) parts and devices, as applied in circuits
within each component for conformance with the de-rating policy of the
GSFC Preferred Parts List (PPL-21). The analyses shall be performed at
the most stressful part-level parameter values that can result from the
specified performance and environmental requirements on the assembly or
component. The analyses shall be performed in close coordination with
the packaging reviews and shall be required input data for
component-level design reviews. The analyses shall be documented and
maintained at the Contractor's facility for the GSFC LDCM Project
review.

### Worst-Case Analyses

The Contractor shall perform worst-case analyses for critical parameters
that are subject to variations that could degrade performance, where
failure results in a severity category of 2 or higher, and provides data
that question the flightworthiness of the design (refer to Table 4-1).
Analyses or test or both shall demonstrate adequacy of margins in the
design of electronic circuits, optics, electromechanical and mechanical
items (mechanisms). The analyses shall consider all parameters set at
worst‑case limits and worst‑case environmental stresses for the
parameter or operation being evaluated. The analyses shall be updated in
keeping with design changes. The analyses and updates shall be presented
at applicable design reviews.

### Software Reliability

The Contractor shall implement a software reliability program addressing
the tolerance of minor defects and the complete removal of critical
defects. The software reliability program shall monitor and control
defect removal, field performance, and include a model to predict the
bug removal rate or number of bugs remaining based on testing, running
time, or bug count. The software reliability model may be:

a.  Time domain (related to the number of bugs at a given time during
    development)

b.  Data domain (estimated by running the program for a subset of input
    data)

c.  Axiomatic (based on laws/rules applied during the programming
    process)

d.  Based other methods resulting from input data sets, logic paths,
    etc.

The Contractor shall document actions to verify that the software design
and software engineering techniques improve the duration or probability
of failure free performance and ensure repeatability of the software.

### Reliability Block Diagram

The Contractor shall develop a Reliability Block Diagram that address
both mission failures and degraded modes of operation. Reliability block
diagram (RBD) analyses shall be used to (1) quantify system reliability
and function; (2) assess the level of failure tolerance achieved
(redundancy); (3) identify intersystem disconnects as well as areas of
incomplete design definition, and (4) perform trade-off studies to
optimize reliability and cost. For the initial assessments, the
contractor shall use the parts count reliability prediction methodology
of MIL-HDBK-217. As the design matures, a complete RBD, failure
definitions, and mathematical models shall be developed in accordance
with MIL-HDBK-217.

## RELIABILITY ANALYSIS OF TEST DATA

Information acquired during the normal test program shall be fully
utilized to assess flight equipment reliability performance and identify
potential or existing problem areas.

### Trend Analyses

Trend analyses shall be performed to the component level to track
measurable parameters that relate to performance stability. Selected
parameters shall be monitored for trends starting at component
acceptance testing and continuing during the system integration and test
phases. The monitoring shall be accomplished within the normal test
framework (i.e., during functional tests, environmental tests, etc). The
reliability trending program shall be merged with the performance
trending program in accordance with the CDRL. A system shall be
established for tracking total operational time and recording and
analyzing the parameters, as well as any changes from the first observed
value, even if the levels are within specified limits. The Contractor
shall deliver a list of parameters to be monitored and the trend
analysis reports. Trend analysis data shall be reviewed with the mission
operational personnel prior to launch. Analysis of Test Results

Test information, trend data, and failure investigations shall be
analyzed to evaluate reliability implications. Identified problem areas
shall be documented and directed to the attention of project management
for action. This information shall be included in status reports to the
GSFC LDCM Project or it may be a separate monthly report. The results of
the analyses shall be presented at design reviews. The presentations
shall include comments on how the analysis was used to perform design
trade-offs or how the results were taken into consideration when making
design or risk management decisions.

## LIMITED-LIFE ITEMS

The Contractor shall prepare and implement a Limited-Life Plan to
identify and manage limited-life items. The Limited-Life Plan may be
combined with the Reliability Plan and/or the Risk Management Plan, or
maintained as a separate document. Limited-life items include all
hardware that is subject to degradation because of age, operating time,
or cycles such that their expected useful life is less than twice the
required life when fabrication, test, storage, and mission operation are
combined. Any items to be used for which the expected life is less than
the mission design life shall be approved by the GSFC LDCM Project via a
waiver.

The Contractor shall maintain a list of limited-life items, which shall
include the following data elements: item, expected life, required life,
duty cycle, rationale for selection and effect on mission parameters. An
item's useful life period begins with fabrication and ends when the
orbital mission is completed.

Records shall be maintained that allow evaluation of the cumulative
stress (time and/or cycles) for limited-life items, starting when useful
life is initiated and indicating the project activity that stresses the
items. Refer to GEVS Section 2.3.5 and 2.4.5.1 for guidance.

## CONTROL OF SUBCONTRACTORS AND SUPPLIERS

The Contractor shall assure that system elements obtained from
subcontractors and suppliers meet the project reliability requirements.
All subcontracts shall include provisions for review and evaluation of
the subcontractor and supplier reliability efforts.

Reliability requirements shall be tailored in hardware and software
subcontracts for the project and shall exercise necessary surveillance
to ensure that subcontractor and supplier reliability efforts are
consistent with overall system requirements. As a result of this
tailoring, the Contractor shall:

-   Incorporate quantitative reliability requirements in subcontracted
    equipment specifications

-   Ensure that subcontractors have reliability programs that are
    compatible with the overall program

-   Review subcontractor assessments and analyses for accuracy and
    correctness of approach

-   Review subcontractor test plans, procedures, and reports for
    correctness of approach and test details

-   Attend and participate in subcontractor design reviews

-   Ensure that subcontractors comply with the applicable system
    reliability requirements during the project operational phase

# SOFTWARE ASSURANCE REQUIREMENTS

## GENERAL REQUIREMENTS

The Contractor shall prepare a Software Development and Management Plan
(SDMP) that addresses software development and software assurance
functions in compliance with ANSI/ISO/ASQ 9001-2000, or equivalent. The
SDMP shall be applied to software and firmware developed for the LDCM
Project.

## SOFTWARE TECHNICAL REVIEWS

A program of software engineering working-level peer reviews shall be
implemented throughout the development life cycle to identify and
resolve concerns prior to formal system level reviews. Topics that shall
be addressed in the peer reviews include:

1.  Design verification

2.  Coding

3.  Analyses and studies

4.  Safety

5.  Risk assessment, resolution and contingency plans

6.  Procurements

7.  Configuration management

8.  Testability and test planning (including test anomalies and
    resolution)

Software systems reviews shall be integrated with the major technical
review program.

Topics to be addressed at PDR:

1.  Software documentation in compliance with the Configuration
    Management Plan

2.  Software, both instrument-based, GSE-based, and external, necessary
    to operate, test, calibrate, design, and analyze the instrument

3.  Compatibility of instrument software with the spacecraft (S/C), and
    for operation and calibration through the ground data information
    system

4.  Software necessary to analyze instrument test data and for in-flight
    engineering analysis

5.  Software capability to provide all instrument operational modes

6.  Software required for operations analyses utilizing the System Test
    Equipment (STE)

7.  Software for supporting instrument verification, integration,
    monitoring of performance, ground operations, as well as supporting
    evaluation of data acquired during S/C integration and flight
    operations

8.  Providing and maintaining real-time and off-line software for
    instrument calibration

9.  Calibration in all channels

10. Software for a formatted real-time data dump

11. Software test plan

At CDR, the Contractor shall provide updates of items required for SWPDR
and definition of the test procedures and test cases to be used with
each type of testing (unit, integration, and acceptance).

## SOFTWARE QUALITY ASSURANCE (SQA)

The Contractor shall provide, as part of the SDMP, an SQA plan that
describes how the software quality assurance activities will be planned,
implemented, and documented. The SQA program shall:

1.  Ensure that assurance requirements are documented and satisfied
    throughout all phases of the development life cycle

2.  Detect actual or potential conditions that could degrade quality,
    including deficiencies and system incompatibilities, and provide a
    process to ensure corrective action is taken and completed

3.  Ensure timely and effective preventive action by identifying root
    causes of deficiencies and nonconformance

4.  Ensure standards and procedures for management, engineering and
    assurance activities are specified and compliance by management and
    engineering personnel is verified

## SOFTWARE VERIFICATION AND VALIDATION

The Contractor shall prepare and maintain a Software Performance
Verification Matrix as a part of the System Performance Verification
Matrix that shows the flow-down of each software system performance
requirement and the verification process (refer to Section 9.2.1.1).V&V
activities shall be performed during each phase of the software life
cycle and shall include the following:

1.  Analysis of system and software requirements allocation,
    verifiability, testability, completeness, and consistency (including
    analysis of test requirements)

2.  Design and code analysis including design completeness and
    correctness

3.  Interface analysis (requirements and design levels)

4.  Formal Inspections

5.  Formal Reviews (phase transition reviews)

6.  Test planning, performance, and reporting

Access to information shall be provided when requested by the GSFC LDCM
Project for the NASA Independent Verification and Validation (IV&V)
effort. Electronic access to the information shall be permitted.

## SAFETY ASSURANCE

If any component is identified as safety critical, the Contractor shall
conduct a software safety program on that component that complies with
NASA-STD-8719.13A "NASA Software Safety Standard\". Refer to Section
3.10 for additional software safety requirements.

## GFE, EXISTING AND PURCHASED SOFTWARE/FIRMWARE (SW/FW)

If the Contractor is provided SW/FW as government-furnished equipment
(GFE), or will use existing or purchased SW/FW; the Contractor shall
ensure that the SW/FW meets the functional, performance, and interface
requirements placed upon it. This SW/FW shall meet all applicable
standards, including those for design, code, and documentation; or a
waiver to those standards shall be submitted for GSFC LDCM Project
approval. Any significant modification to any piece of the existing
SW/FW shall be subject to all of the provisions of the Contractor's SQA
plan and the provisions of this MAR. The definition of a significant
modification is a change of 20% of the source lines of code in the
SW/FW.

# PARTS REQUIREMENTS

## GENERAL REQUIREMENTS

The Contractor shall plan and implement an Electrical, Electronic, and
Electromechanical (EEE) Parts Control to ensure that all parts selected
for use in flight hardware meet mission objectives for quality and
reliability for a Quality Level 2 Mission.

The Contractor shall prepare a Parts Control Plan (PCP) describing the
approach and methodology for implementing the Parts Control Program. The
PCP shall define the criteria for parts selection and approval based on
the guidelines in this chapter. The PCP shall be made available for the
LDCM Project review at the Contractor's facility.

## ELECTRICAL, ELECTRONIC, AND ELECTROMECHANICAl (EEE) parts

The NASA Parts Selection List (NPSL) has been developed to serve as a
parts selection tool for design engineers and parts engineers supporting
NASA space flight programs. The NPSL provides a detailed listing of EEE
part types which the NASA EEE Parts Assurance Group (NEPAG) recommends
for NASA flight projects based on evaluations, risk assessments and
quality levels. In general, the parts listed in the NPSL:

-   Have established procurement specifications

-   Have available source(s) of supply

-   Are capable of meeting a wide range of application needs

-   Have been assessed for quality, reliability, and risk and found to
    meet the criteria for listing

Custom or advanced technology devices such as custom hybrid
microcircuits, detectors, Application Specific Integrated Circuits
(ASIC), and Multi-Chip Modules (MCM) shall also be subject to parts
control appropriate for the individual technology.

### Quality Level

The parts reliability requirement is Quality Level 2. This was
determined in accordance with EEE-INST-002. This document provides
detailed instructions for the selection and testing of electronic parts
to be used in GSFC space flight programs depending on mission
requirements. The NPSL may be used as a vehicle for parts selection to
the specified quality levels.

### Parts Control Board

The Contractor shall establish a Parts Control Board (PCB). The PCB
shall manage and control usage of EEE parts for the LDCM project. The
PCB shall approve all parts to be used to ensure that the mission
requirements have been met. The PCB shall meet regularly to concur,
resolve, and document any issues necessary for compliance. The PCB shall
be responsible for developing and maintaining a LDCM Project Approved
Parts List (PAPL) including responsibility for all parts activities such
as failure investigations, disposition of non-conformances, and problem
resolutions.

The PCB operating procedures shall be included as part of the PCP.
Meeting minutes or records shall be maintained to document all decisions
made and a copy provided to the GSFC LDCM Project Systems Assurance
Manager (SAM) within five working days of convening the meeting. These
minutes shall be placed into the project parts database. The project SAM
retains the right to overturn decisions involving nonconformance within
ten days after receipt of meeting minutes.

### Parts Selection and Processing

The Contractor shall select and process all parts in accordance with the
EEE-INST-002 \"Instructions for EEE Parts Selection, Screening,
Qualification and Derating\". All application notes in EEE-INST-002
shall apply. Parts shall be procured to Quality Level 2 as defined in
EEE-INST-002 unless otherwise justified and approved by the PCB in
accordance with the reliability program. These requirements shall then
become the established criteria for parts selection, testing, and
approval for the duration of the project, and shall be documented in the
PCP. Parts selected from the NASA Parts Selection List and the GSFC
Preferred Parts List (PPL-21) are considered to have met all criteria of
EEE-INST-002 for the appropriate parts quality level, and may be
approved by the PCB provided all mission application requirements
(performance, de-rating, radiation, etc.) are met. If the parts to be
used on the Engineering Models are procured by methods 1 through 4 of
EEE-INST-002, full paperwork and documentation (i.e. pedigree) are not
required.

#### Custom Devices

In addition to applicable requirements of EEE-INST-002, custom
microcircuits, hybrid microcircuits, MCM, ASIC, etc. planned for use
shall be subjected to a design review. The review may be conducted as
part of the PCB activity. The design review shall address, at a minimum,
de-rating of elements, method used to assure each element reliability,
assembly process and materials, and method for assuring adequate thermal
matching of materials.

### De-rating

All EEE parts shall be used in accordance with the de-rating guidelines
of the GSFC Preferred Parts List (PPL-21). The Contractor's de-rating
policy may be used in place of the GSFC Preferred Parts List guidelines
and shall be submitted with the PCP. Documentation on parts de-rating
analyses shall be maintained and available for GSFC LDCM Project review.

### Radiation Hardness

All parts shall be selected to meet their intended application in the
predicted mission radiation environment. The radiation environment
consists of two separate effects, those of total ionizing dose and
single-event effects. Analyses for each part with respect to both
effects shall be documented. The possibility of displacement damage
shall also be considered for parts susceptible to these effects.

### Verification Testing

Verification of screening or qualification tests by re-testing is not
required unless deemed necessary as indicated by failure history,
Government-Industry Data Exchange Program (GIDEP) Alerts, or other
reliability concerns. If required, testing shall be in accordance with
EEE-INST-002 as determined by the PCB. The Contractor, however, shall be
responsible for the performance of supplier audits, surveys, source
inspections, witnessing of tests, and/or data review to verify
conformance to established requirements.

### Destructive Physical Analysis (DPA)

A Destructive Physical analysis (DPA) shall be required for a sample of
components identified based on failure history, construction concerns,
vendor information, recent GIDEP alerts or advisories, or other
reliability concerns. The DPA should be performed upon receipt of parts
or prior to kitting.

A sample of each lot date code of microcircuits, hybrid microcircuits,
and semiconductor devices shall be subjected to a DPA. DPA tests,
procedures, sample size and criteria shall be as specified in GSFC
specification S-311-M-70, Destructive Physical Analysis. Contractor's
procedures for DPA may be used in place of S-311-M-70 and shall be
submitted with the PCP. Variation to the DPA sample size requirements,
due to part complexity, availability, or cost, shall be determined and
approved by the PCB on a case-by-case basis. As required by the LDCM
Project, the Contractor may provide the required number of DPA samples
to GSFC for DPA. This shall be accomplished on a case-by-case basis
through mutual agreement by the Contractor and GSFC.

### Failure Analysis

Failure analyses shall be performed by experienced personnel and shall
support the nonconformance reporting system. The failure analysis
laboratory (in-house or out-of-house) shall be equipped to analyze parts
to the extent necessary to ensure an understanding of the failure mode
and cause. The failure analyses shall be available to GSFC LDCM Project
for review upon request.

### Parts Age Control

The Contractor shall develop a parts age control process. Prior to use,
the PCB shall determine the required additional screening or lot sample
testing based on the part type, complexity, expected failure mechanisms,
and available data.

Parts drawn from controlled storage after 5 years from the date of the
last full screen shall be subjected to a full 100 percent re-screen and
sample DPA. Alternative test plans may be used as determined and
approved by the PCB on a case-by-case basis. Parts over 10 years from
the date of the last full screen or stored in other than controlled
conditions where they are exposed to the elements or sources of
contamination shall be submitted to the PCB for approval prior to use.

## PARTS LIST

The Contractor shall create and maintain a Project Approved Parts List
(PAPL) and/or a Parts Identification List (PIL) for the duration of the
contract. The PAPL and PIL may be incorporated into one list, which
shall be submitted to GSFC LDCM Project as a PIL, provided clear
distinctions are made as to parts approval status and whether parts are
planned for use in flight hardware.

### Project Approved Parts List

The PAPL shall be the only source of approved parts for project flight
hardware, but may contain parts not actually in flight designs. Only
parts that have been evaluated and approved by the PCB shall be listed
in the PAPL. Parts must be approved for listing on the PAPL before
initiation of procurement activity. The criteria for PAPL listing shall
be based on EEE-INST-002 and as specified herein. The PCB will ensure
standardization and the maximum use of parts listed in the PAPL. The
PAPL and all subsequent revisions shall be available for GSFC LDCM
Project review upon request.

### Parts Identification List

As opposed to the PAPL, the PIL shall list all parts planned for use in
flight hardware regardless of their approval status. The initial PIL and
subsequent updates shall be submitted to GSFC in accordance with the
contract delivery requirements. The Contractor shall provide the process
as to how the PIL will be shared with GSFC's parts organizations.

### As-Built Parts List

In addition to the PAPL and PIL, an ABPL shall be prepared and submitted
to GSFC in accordance with the contract delivery requirements. The ABPL
identifies parts actually used in flight hardware with additional
as-built information, such as parts manufacturers, lot date code and
locations (circuit designations) where the parts are used in the
hardware.

### Parts List Information

Each parts list shall be a composite of the parts selections for each
circuit design in the component, including EEE parts. As a minimum, each
list shall contain the following information:

a.  Part number

b.  Description

c.  Next assembly

d.  Trace ID

e.  Quantity issued/used

f.  Serial Number

g.  Order Type

h.  P.O. Number

i.  Name or Commercial and Government Entity (CAGE) Code of the part
    manufacturer

j.  Manufacturing lot date code

k.  Vendor ID

l.  System used

m.  Part specification control drawing number

n.  Common designator or generic number

o.  Drawing number of component to which the list pertains

## GIDEP ALERTS AND PROBLEM ADVISORIES

The Contractor shall participate in the Government/Industry Data
Exchange Program (GIDEP). Copies of documentation relevant to the LDCM
hardware that are sent to GIDEP shall be provided to the GSFC LDCM
Project SAM.

The Contractor shall review and disposition all GIDEP Alerts and Problem
Advisories for impact on flight equipment. New parts procurements and
parts pulled from storage shall be continuously checked for impact.
Parts pulled from inventory for flight shall have the alert history
checked for the period dating back to the date code marked on the parts.
In addition, the Contractor shall review and disposition any NASA Alerts
and Advisories. Alert applicability, impact, and corrective actions
shall be documented and status provided to the GSFC LDCM Project on a
monthly basis. In the event of a conflict between GIDEP alerts and NASA
Advisories, the NASA Advisory shall govern.

Sufficient records shall be maintained to determine applicability of any
GIDEP alerts related to parts and materials selected or used for LDCM.

# MATERIALS, PROCESSES, AND LUBRICATION REQUIREMENTS

## GENERAL REQUIREMENTS

The Contractor shall plan and implement a comprehensive Materials and
Processes Control Program (M&PCP) beginning at the design stage of the
hardware to help ensure the success and safety of the LDCM mission by
the appropriate selection, processing, inspection, and testing of the
materials and lubricants for use in flight hardware. The M&PCP Plan
shall be made available for the LDCM Project review at Contractor's
facility. The GSFC LDCM Project Materials Assurance Engineer (MAE)
review and approval by the Government CO is required for each material
and lubrication usage or application in LDCM flight hardware.

## MATERIALS SELECTION REQUIREMENTS

In order to anticipate and minimize materials problems during space
hardware development and operation, the Contractor shall, when selecting
materials and lubricants, consider potential problem areas such as
radiation effects, thermal cycling, stress corrosion cracking, galvanic
corrosion, hydrogen embrittlement, lubrication, contamination, composite
materials, atomic oxygen, useful life, vacuum outgassing, toxic
offgassing, flammability and fracture toughness, as well as the
properties required by each material usage or application.

### Material Identification List (MIL)

The Contractor shall maintain a Materials Identification List (MIL) of
all materials planned for use in flight hardware, regardless of their
approval status. An As-Built Materials List (ABML) shall also be
prepared and submitted to GSFC LDCM Project in accordance with the
contract delivery requirements. The ABML identifies materials and
lubricants actually used in flight hardware with additional as-built
information such as materials manufacturers and lot date codes.

The MIL shall include a Polymeric Materials and Composites Usage List,
an Inorganic Materials and Composites Usage List, a Lubrication Usage
List, and a Materials Process Utilization List.

### Compliant Materials

Compliant materials shall be used in the fabrication of flight hardware
to the extent practicable. In order to be compliant, a material must be
used in a conventional application and meet the applicable selection
criteria identified in Table 7.1. A compliant material does not require
a Materials Usage Agreement (MUA).

[]{#__RefHeading___Toc75054522 .anchor}Table 7‑2. Material Selection
Criteria

+----------+----------+---------------+------------+-----------------+
| Type     | Payload  | Flammability  | Vacuum     | Stress          |
|          |          | and           |            | Corrosion       |
| Launch   | Location |               | Outgassing |                 |
|          |          | Toxic         |            | Cracking (SCC)  |
|          |          | Offgassing    |            |                 |
+----------+----------+---------------+------------+-----------------+
| ELV      | All      | Note 1        | Note 2     | Note 3          |
+----------+----------+---------------+------------+-----------------+

NOTES:

1.  Hazardous materials requirements, including flammability, toxicity
    and compatibility as specified in Eastern and Western Range 127-1
    Range Safety Requirements, Sections 3.10 and 3.12.

2.  Vacuum Outgassing requirements as defined in Section 7.2.6.2.

3.  Stress corrosion cracking requirements as defined in MSFC-SPEC-522.

### Non-compliant Materials

A material that does not meet the requirements of the applicable
selection criteria of Table 7.1, or meets the requirements of Table 7.1
but is used in an unconventional application, shall be considered to be
a non-compliant material. The proposed use of a non-compliant material
requires that a Materials Usage Agreement (Figure 7-1) and/or a Stress
Corrosion Evaluation Form (Figure 7-2) or Contractor\'s equivalent form,
be submitted for review and approval by the GSFC LDCM Project MAE.

#### Materials Used in "Off-the-Shelf-Hardware"

\"Off-the-shelf hardware\" for which a detailed materials list is not
available and where the included materials cannot be easily identified
and/or changed shall be treated as non-compliant. A MUA shall be
prepared and submitted to define what measures will be used to ensure
that all materials in the hardware are acceptable for use. Such measures
might include any one, or a combination, of the following: hermetic
sealing, vacuum bake-out, material changes for known non-compliant
materials, etc. When a vacuum bake-out is the selected method, it shall
incorporate a quartz crystal microbalance (QCM) and cold finger to
enable a determination of the duration and effectiveness of the bake-out
as well as compliance with the contractor's Contamination Control Plan
(Data Item Description SA-13) and error budget.

### Conventional Applications

Conventional applications or usage of materials is the use of compliant
materials in a manner for which there is extensive satisfactory
aerospace heritage.

### Non-conventional Applications

The proposed use of a compliant material for an application for which
there is limited satisfactory aerospace usage shall be considered a
non-conventional application. In that case, the material usage shall be
verified for the desired application on the basis of test, similarity,
analyses, inspection, existing data, or a combination of those methods.

### Polymeric Materials

A polymeric materials and composites usage list (Figure 7-3), or
equivalent, shall be prepared and submitted as a part of the MIL for MAE
review and approval. Material acceptability shall be determined on the
basis of flammability, toxic offgassing, vacuum outgassing, and all
other materials properties relative to the application requirements and
usage environment.

#### Flammability and Toxic Offgassing

Material flammability and toxic offgassing shall be determined in
accordance with the test methods described in NASA-STD-6001. ELV payload
materials shall meet the requirements of Eastern and Western Range 127-1
Range Safety Requirements, Sections 3.10 and 3.12.

#### Vacuum Outgassing

Material vacuum outgassing shall be determined in accordance with ASTM
E-595. In general, a material is qualified on a product-by-product
basis. However, if lot variation of any material is suspected, then lot
testing may be required. In such cases, material approval is contingent
upon the lot testing results. Only materials have a total mass loss
(TML) less than 1.00% and a collected volatile condensable mass (CVCM)
less than 0.10% shall be approved for use in a vacuum environment unless
application considerations listed on a MUA dictate otherwise.

#### Shelf-Life-Controlled Materials

Polymeric materials that have a limited shelf-life shall be controlled
by a process that identifies the start date (manufacturer\'s processing,
shipment date, or date of receipt, etc.), the storage conditions
associated with a specified shelf-life, and expiration date. Materials
such as o-rings, rubber seals, tape, uncured polymers, lubricated
bearings and paints shall be included. The use of materials with expired
date code requires a demonstration, by means of appropriate tests, that
the properties of the materials have not been compromised for their
intended use. Such materials shall be approved by the M&PCB prior to
use. When a limited-life piece part is installed in a subassembly, the
subassembly item shall be included in the Limited-Life Items List (refer
to Section 4.6).

### Inorganic Materials

An inorganic materials and composites usage list (Figure 7-4), or
equivalent, shall be prepared and submitted as a part of the MIL for MAE
review and approval prior to use. In addition, the Contractor may be
requested to submit supporting applications data. The criteria specified
in MSFC-SPEC-522 shall be used to determine that metallic materials meet
the stress corrosion cracking (SCC) criteria. An MUA (Figure 7-1) and
SCC evaluation (Figure 7-2) shall be submitted for GSFC LDCM Project MAE
review and Government CO approval for each material usage that does not
comply with the MSFC-SPEC-522 SCC requirements.

#### Fasteners

The Contractor shall comply with the procurement documentation and test
requirements for flight hardware and critical ground support equipment
fasteners outlined in 541-PG-8072.1.2, Goddard Space Flight Center
Fastener Integrity Requirements (formerly GSFC S-313-100). For a copy of
541-PG-8072.1.2, use the following hyperlink \-\--
<http://gdms.gsfc.nasa.gov/gdms/plsql/masterlist.menu>. Material test
reports for fastener lots shall be submitted to the GSFC LDCM Project
MAE for review upon request.

Fasteners made of plain carbon or low alloy steel shall be protected
from corrosion. When plating is specified, it shall be compatible with
the space environment. On steels harder than RC 33, plating shall be
applied by a process that is not embrittling to the steel.

### Lubrication

A lubrication usage list (Figure 7.5), or equivalent, shall be prepared
and submitted as a part of the MIL for MAE review and approval. Also,
supporting applications data shall be submitted, upon request.

Lubricants shall be selected for use with materials on the basis of
valid test results that confirm the suitability of the composition and
the performance characteristics for each specific application, including
compatibility with the anticipated environment and contamination
effects.

All lubricated mechanisms shall be qualified by life testing; or
heritage of an identical mechanism used in identical applications.
Evidence of qualification must be provided for GSFC LDCM Project MAE
review.

## PROCESS SELECTION REQUIREMENTS

The Contractor shall prepare and submit a material process utilization
list (Figure 7-6), or equivalent, as a part of the MIL for MAE review
and approval. A copy of any process shall be submitted to the MAE for
review upon request. Manufacturing processes (e.g., lubrication, heat
treatment, welding, and chemical or metallic coatings) shall be
carefully selected to prevent any unacceptable material property changes
that could cause adverse effects of materials applications.

## PROCUREMENT REQUIREMENTS

### Purchased Raw Materials

The results of nondestructive chemical and physical tests; or a
Certificate of Compliance (COC) shall accompany raw materials. This
information need only be provided to the GSFC LDCM Project when there is
a direct question concerning the material's flightworthiness.

### Raw Materials Used in Purchased Products

The Contractor shall require that their suppliers meet the requirements
of Section 7.4.1 of this document and provide copies of the results of
acceptance tests and analyses performed on raw material; or the
Certificates of Compliance (COCs), unless waived by the CO/COTR.

  --------------- ----------- -------------- -------- ------------- ---------- ---------- -------------- ------------- ------------- -------------- --------------- ---------
  **MATERIAL                                          USAGE                                                                                         PAGE OF         
  USAGE                                               AGREEMENT                                                                                                     
  AGREEMENT**                                         NO.:                                                                                                          

  PROJECT:                    SUBSYSTEM:              ORIGINATOR:                                                                                   ORGANIZATION:   

  DETAIL DRAWING              NOMENCLATURE                                     USING                                                 NOMENCLATURE                   
                                                                               ASSEMBLY                                                                             

                                                                                                                                                                    

  MATERIAL &                                                                              MANUFACTURER &                                                            
  SPECIFICATION                                                                           TRADE NAME                                                                

                                                                                                                                                                    

  USAGE           THICKNESS                  WEIGHT                 EXPOSED                              ENVIRONMENT                                                
                                                                    AREA                                                                                            

                                                                                                         PRESSURE      TEMPERATURE                                  MEDIA

                                                                                                                                                                    

  APPLICATION:                                                                                                                                                      

  RATIONALE:                                                                                                                                                        

  ORIGINATOR:                                                       PROJECT                                                                         DATE:           
                                                                    MANAGER:                                                                                        
  --------------- ----------- -------------- -------- ------------- ---------- ---------- -------------- ------------- ------------- -------------- --------------- ---------

[]{#__RefHeading___Toc75054500 .anchor}Figure 7‑1. MUA

**STRESS CORROSION EVALUATION FORM**

1\. Part Number

2\. Part Name

3\. Next Assembly Number

4\. Manufacturer

5\. Material

6\. Heat Treatment

7\. Size and Form

8\. Sustained Tensile Stresses-Magnitude and Direction

> a\. Process Residual
>
> b\. Assembly
>
> c\. Design, Static

9\. Special Processing

10\. Weldments

> a\. Alloy Form, Temper of Parent Metal
>
> b\. Filler Alloy, if none, indicate
>
> c\. Welding Process
>
> d\. Weld Bead Removed - Yes ( ), No ( )
>
> e\. Post-Weld Thermal Treatment
>
> f\. Post-Weld Stress Relief \_

11\. Environment

12\. Protective Finish

13\. Function of Part

14\. Effect of Failure

15\. Evaluation of Stress Corrosion Susceptibility

16\. Remarks:

[]{#__RefHeading___Toc75054501 .anchor}Figure 7‑2. Stress Corrosion
Evaluation Form

<table>
<colgroup>
<col style="width: 4%" />
<col style="width: 19%" />
<col style="width: 14%" />
<col style="width: 12%" />
<col style="width: 7%" />
<col style="width: 15%" />
<col style="width: 6%" />
<col style="width: 5%" />
<col style="width: 2%" />
<col style="width: 2%" />
<col style="width: 0%" />
<col style="width: 2%" />
<col style="width: 3%" />
<col style="width: 1%" />
</colgroup>
<tbody>
<tr class="odd">
<td colspan="14">POLYMERIC MATERIALS AND COMPOSITES USAGE LIST</td>
</tr>
<tr class="even">
<td colspan="7">SPACECRAFT SYSTEM/EXPERIMENT GSFC T/O</td>
<td></td>
<td colspan="3"></td>
<td colspan="2"></td>
<td></td>
</tr>
<tr class="odd">
<td colspan="7"></td>
<td>Area, cm<sup>2</sup></td>
<td colspan="3">Vol., cc</td>
<td colspan="2">Wt., gm</td>
<td></td>
</tr>
<tr class="even">
<td colspan="7">DEVELOPER/CONTRACTOR ADDRESS</td>
<td></td>
<td colspan="3"></td>
<td colspan="2"></td>
<td></td>
</tr>
<tr class="odd">
<td colspan="7"></td>
<td>1 0-1</td>
<td colspan="3">A 0-1</td>
<td colspan="2">a 0-1</td>
<td></td>
</tr>
<tr class="even">
<td colspan="7">PREPARED BY PHONE DATE</td>
<td>2 2-100</td>
<td colspan="3">B 2-50</td>
<td colspan="2">b 2-50</td>
<td></td>
</tr>
<tr class="odd">
<td colspan="7">PREPARED</td>
<td>3 101-1000</td>
<td colspan="3">C 51-500</td>
<td colspan="2">c 51-500</td>
<td></td>
</tr>
<tr class="even">
<td colspan="7">DATE DATE</td>
<td>4 &gt;1000</td>
<td colspan="3">D &gt;500</td>
<td colspan="2">d &gt;500</td>
<td></td>
</tr>
<tr class="odd">
<td colspan="7">GSFC MATERIALS EVALUATOR PHONE RECEIVED EVALUATED</td>
<td></td>
<td colspan="3"></td>
<td colspan="2"></td>
<td></td>
</tr>
<tr class="even">
<td><p>ITEM</p>
<p>NO.</p></td>
<td>MATERIAL IDENTIFICATION<sup>(2)</sup></td>
<td>MIX FORMULA<sup>(3)</sup></td>
<td>CURE<sup>(4)</sup></td>
<td><p>AMOUNT</p>
<p>CODE</p></td>
<td>EXPECTED ENVIRONMENT<sup>(5)</sup></td>
<td colspan="3"><p>REASON</p>
<p>FOR SELECTION<sup>(6)</sup></p></td>
<td colspan="5">OUTGASSING VALUES</td>
</tr>
<tr class="odd">
<td></td>
<td></td>
<td></td>
<td></td>
<td></td>
<td></td>
<td colspan="3"></td>
<td colspan="3">TML</td>
<td colspan="2">CVCM</td>
</tr>
<tr class="even">
<td></td>
<td></td>
<td></td>
<td></td>
<td></td>
<td></td>
<td colspan="3"></td>
<td colspan="3"></td>
<td colspan="2"></td>
</tr>
<tr class="odd">
<td></td>
<td colspan="8"><blockquote>
<p><strong>NOTES</strong></p>
<p>1. List all polymeric materials and composites applications utilized
in the system except lubricants which should be listed on polymeric and
composite materials usage list.</p>
<p>2. Give the name of the material, identifying number and
manufacturer. Example: Epoxy, Epon 828, E. V. Roberts and Associates</p>
<p>3. Provide proportions and name of resin, hardener (catalyst),
filler, etc. Example: 828/V140/Silflake 135 as 5/5/38 by weight</p>
<p>4. Provide cure cycle details. Example: 8 hrs. at room temperature +
2 hrs. at 150C</p>
<p>5. Provide the details of the environment that the material will
experience as a finished S/C component, both in ground test and in
space. List all materials with the same environment in a group. Example:
T/V : -20C/+60C, 2 weeks, 10E-5 torr, ultraviolet radiation (UV)<br />
Storage: up to 1 year at room temperature<br />
Space: -10C/+20C, 2 years, 150 mile altitude, UV, electron, proton,
atomic oxygen</p>
<p>6. Provide any special reason why the materials was selected. If for
a particular property, please give the property.<br />
Example: Cost, availability, room temperature curing or low thermal
expansion.</p>
</blockquote></td>
<td></td>
<td colspan="2"></td>
<td colspan="2"></td>
</tr>
<tr class="even">
<td></td>
<td></td>
<td></td>
<td></td>
<td></td>
<td></td>
<td colspan="3"></td>
<td colspan="3"></td>
<td colspan="2"></td>
</tr>
</tbody>
</table>

GSFC 18-59B 3/78

[]{#__RefHeading___Toc75054502 .anchor}Figure 7‑3. Polymeric Materials
and Composites Usage List

+---+------------+-----------+-----------+-----------+----+----+------+
| I |            |           |           |           |    |    |      |
| N |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| G |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| N |            |           |           |           |    |    |      |
| I |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| M |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| I |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| L |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| N |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| M |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| I |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| U |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| G |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| L |            |           |           |           |    |    |      |
| I |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
|   |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| F |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| Y |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| M |            |           |           |           |    |    |      |
| / |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| X |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| I |            |           |           |           |    |    |      |
| M |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| N |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| G |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| F |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| / |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
|   |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| V |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| L |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| / |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| N |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
|   |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| B |            |           |           |           |    |    |      |
| Y |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| H |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| N |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
|   |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
|   |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
|   |            |           |           |           |    |    |      |
| G |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| F |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| M |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| I |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| L |            |           |           |           |    |    |      |
| S |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| V |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| L |            |           |           |           |    |    |      |
| U |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| P |            |           |           |           |    |    |      |
| H |            |           |           |           |    |    |      |
| O |            |           |           |           |    |    |      |
| N |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| R |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| C |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| I |            |           |           |           |    |    |      |
| V |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| V |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| L |            |           |           |           |    |    |      |
| U |            |           |           |           |    |    |      |
| A |            |           |           |           |    |    |      |
| T |            |           |           |           |    |    |      |
| E |            |           |           |           |    |    |      |
| D |            |           |           |           |    |    |      |
+---+------------+-----------+-----------+-----------+----+----+------+
| I | MATERIAL   | CONDI     | APPLICA   | EXPECTED  | S. | M  | NDE  |
| T | IDENTIFIC  | TION^(3)^ | TION^(4)^ | ENVIRON   | C. | UA |      |
| E | ATION^(2)^ |           |           | MENT^(5)^ | C. |    | ME   |
| M |            |           | OR OTHER  |           | T  | N  | THOD |
|   |            |           | SPEC. NO. |           | AB | O. |      |
| N |            |           |           |           | LE |    |      |
| O |            |           |           |           | N  |    |      |
| . |            |           |           |           | O. |    |      |
+---+------------+-----------+-----------+-----------+----+----+------+
|   |            |           |           |           |    |    |      |
+---+------------+-----------+-----------+-----------+----+----+------+
|   | > NOTES:   |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | > 1\. List |           |           |           |    |    |      |
|   | > all      |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  inorganic |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  materials |           |           |           |    |    |      |
|   | > (metals, |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  ceramics, |           |           |           |    |    |      |
|   | > glasses, |           |           |           |    |    |      |
|   | > liquids, |           |           |           |    |    |      |
|   | > and      |           |           |           |    |    |      |
|   | > met      |           |           |           |    |    |      |
|   | al/ceramic |           |           |           |    |    |      |
|   | > c        |           |           |           |    |    |      |
|   | omposites) |           |           |           |    |    |      |
|   | > except   |           |           |           |    |    |      |
|   | > bearing  |           |           |           |    |    |      |
|   | > and      |           |           |           |    |    |      |
|   | > l        |           |           |           |    |    |      |
|   | ubrication |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  materials |           |           |           |    |    |      |
|   | > that     |           |           |           |    |    |      |
|   | > should   |           |           |           |    |    |      |
|   | > be       |           |           |           |    |    |      |
|   | > listed   |           |           |           |    |    |      |
|   | > on Form  |           |           |           |    |    |      |
|   | > 18-59C.  |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | > 2\. Give |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  materials |           |           |           |    |    |      |
|   | > name,    |           |           |           |    |    |      |
|   | > i        |           |           |           |    |    |      |
|   | dentifying |           |           |           |    |    |      |
|   | > number   |           |           |           |    |    |      |
|   | > manu     |           |           |           |    |    |      |
|   | facturer.\ |           |           |           |    |    |      |
|   | > Example: |           |           |           |    |    |      |
|   | > a.       |           |           |           |    |    |      |
|   | > Aluminum |           |           |           |    |    |      |
|   | > 6061-T6\ |           |           |           |    |    |      |
|   | > b.       |           |           |           |    |    |      |
|   | > E        |           |           |           |    |    |      |
|   | lectroless |           |           |           |    |    |      |
|   | > nickel   |           |           |           |    |    |      |
|   | > plate,   |           |           |           |    |    |      |
|   | > Enplate  |           |           |           |    |    |      |
|   | > Ni 410,  |           |           |           |    |    |      |
|   | > Enthone, |           |           |           |    |    |      |
|   | > Inc.\    |           |           |           |    |    |      |
|   | > c. Fused |           |           |           |    |    |      |
|   | > silica,  |           |           |           |    |    |      |
|   | > Corning  |           |           |           |    |    |      |
|   | > 7940,    |           |           |           |    |    |      |
|   | > Corning  |           |           |           |    |    |      |
|   | > Class    |           |           |           |    |    |      |
|   | > Works    |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | > 3\. Give |           |           |           |    |    |      |
|   | > details  |           |           |           |    |    |      |
|   | > of the   |           |           |           |    |    |      |
|   | > finished |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  condition |           |           |           |    |    |      |
|   | > of the   |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  material, |           |           |           |    |    |      |
|   | > heat     |           |           |           |    |    |      |
|   | > treat    |           |           |           |    |    |      |
|   | > d        |           |           |           |    |    |      |
|   | esignation |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  (hardness |           |           |           |    |    |      |
|   | > or       |           |           |           |    |    |      |
|   | > s        |           |           |           |    |    |      |
|   | trength),\ |           |           |           |    |    |      |
|   | > surface  |           |           |           |    |    |      |
|   | > finish   |           |           |           |    |    |      |
|   | > and      |           |           |           |    |    |      |
|   | > coating, |           |           |           |    |    |      |
|   | > cold     |           |           |           |    |    |      |
|   | > worked   |           |           |           |    |    |      |
|   | > state,   |           |           |           |    |    |      |
|   | > welding, |           |           |           |    |    |      |
|   | > brazing, |           |           |           |    |    |      |
|   | > etc.\    |           |           |           |    |    |      |
|   | > Example: |           |           |           |    |    |      |
|   | > a. Heat  |           |           |           |    |    |      |
|   | > treated  |           |           |           |    |    |      |
|   | > to       |           |           |           |    |    |      |
|   | > Rockwell |           |           |           |    |    |      |
|   | > C 60     |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  hardness, |           |           |           |    |    |      |
|   | > gold     |           |           |           |    |    |      |
|   | > elec     |           |           |           |    |    |      |
|   | troplated, |           |           |           |    |    |      |
|   | > brazed.\ |           |           |           |    |    |      |
|   | > b.       |           |           |           |    |    |      |
|   | > Surface  |           |           |           |    |    |      |
|   | > coated   |           |           |           |    |    |      |
|   | > with     |           |           |           |    |    |      |
|   | > vapor    |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  deposited |           |           |           |    |    |      |
|   | > aluminum |           |           |           |    |    |      |
|   | > and      |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  magnesium |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  fluoride\ |           |           |           |    |    |      |
|   | > c. Cold  |           |           |           |    |    |      |
|   | > worked   |           |           |           |    |    |      |
|   | > to full  |           |           |           |    |    |      |
|   | > hare     |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | condition, |           |           |           |    |    |      |
|   | > TIG      |           |           |           |    |    |      |
|   | > welded   |           |           |           |    |    |      |
|   | > and      |           |           |           |    |    |      |
|   | > e        |           |           |           |    |    |      |
|   | lectroless |           |           |           |    |    |      |
|   | > nickel   |           |           |           |    |    |      |
|   | > plated.  |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | > 4\. Give |           |           |           |    |    |      |
|   | > details  |           |           |           |    |    |      |
|   | > of where |           |           |           |    |    |      |
|   | > on the   |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | spacecraft |           |           |           |    |    |      |
|   | > the      |           |           |           |    |    |      |
|   | > material |           |           |           |    |    |      |
|   | > will be  |           |           |           |    |    |      |
|   | > used     |           |           |           |    |    |      |
|   | > (        |           |           |           |    |    |      |
|   | component) |           |           |           |    |    |      |
|   | > and its  |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | function.\ |           |           |           |    |    |      |
|   | > Example: |           |           |           |    |    |      |
|   | > E        |           |           |           |    |    |      |
|   | lectronics |           |           |           |    |    |      |
|   | > box      |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  structure |           |           |           |    |    |      |
|   | > in       |           |           |           |    |    |      |
|   | > attitude |           |           |           |    |    |      |
|   | > control  |           |           |           |    |    |      |
|   | > system,  |           |           |           |    |    |      |
|   | > not      |           |           |           |    |    |      |
|   | > he       |           |           |           |    |    |      |
|   | rmetically |           |           |           |    |    |      |
|   | > sealed.  |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | > 5\. Give |           |           |           |    |    |      |
|   | > the      |           |           |           |    |    |      |
|   | > details  |           |           |           |    |    |      |
|   | > of the   |           |           |           |    |    |      |
|   | > e        |           |           |           |    |    |      |
|   | nvironment |           |           |           |    |    |      |
|   | > that the |           |           |           |    |    |      |
|   | > material |           |           |           |    |    |      |
|   | > will     |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | experience |           |           |           |    |    |      |
|   | > as a     |           |           |           |    |    |      |
|   | > finished |           |           |           |    |    |      |
|   | > S/C      |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | component, |           |           |           |    |    |      |
|   | > both in  |           |           |           |    |    |      |
|   | > ground   |           |           |           |    |    |      |
|   | > test and |           |           |           |    |    |      |
|   | > in       |           |           |           |    |    |      |
|   | > space.   |           |           |           |    |    |      |
|   | > Exclude  |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  vibration |           |           |           |    |    |      |
|   | > en       |           |           |           |    |    |      |
|   | vironment. |           |           |           |    |    |      |
|   | > List all |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  materials |           |           |           |    |    |      |
|   | > with the |           |           |           |    |    |      |
|   | > same     |           |           |           |    |    |      |
|   | > e        |           |           |           |    |    |      |
|   | nvironment |           |           |           |    |    |      |
|   | > in a     |           |           |           |    |    |      |
|   | > group.\  |           |           |           |    |    |      |
|   | > Example: |           |           |           |    |    |      |
|   | > T/V:     |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | -20C/+60C, |           |           |           |    |    |      |
|   | > 2 weeks, |           |           |           |    |    |      |
|   | > 10E-5    |           |           |           |    |    |      |
|   | > torr,    |           |           |           |    |    |      |
|   | > U        |           |           |           |    |    |      |
|   | ltraviolet |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  radiation |           |           |           |    |    |      |
|   | > (UV)\    |           |           |           |    |    |      |
|   | > Storage: |           |           |           |    |    |      |
|   | > up to 1  |           |           |           |    |    |      |
|   | > year at  |           |           |           |    |    |      |
|   | > room     |           |           |           |    |    |      |
|   | > te       |           |           |           |    |    |      |
|   | mperature\ |           |           |           |    |    |      |
|   | > Space:   |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   | -10C/+20C, |           |           |           |    |    |      |
|   | > 2 years, |           |           |           |    |    |      |
|   | > 150      |           |           |           |    |    |      |
|   | > miles    |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  altitude, |           |           |           |    |    |      |
|   | > UV,      |           |           |           |    |    |      |
|   | >          |           |           |           |    |    |      |
|   |  electron, |           |           |           |    |    |      |
|   | > proton,  |           |           |           |    |    |      |
|   | > Atomic   |           |           |           |    |    |      |
|   | > Oxygen   |           |           |           |    |    |      |
+---+------------+-----------+-----------+-----------+----+----+------+
|   |            |           |           |           |    |    |      |
+---+------------+-----------+-----------+-----------+----+----+------+

GSFC 18-59A 3/78

[]{#__RefHeading___Toc75054503 .anchor}Figure 7‑4. Inorganic Materials
and Composites Usage List

+---+------------+------------+----------+-------+------+-----+------+
| L |            |            |          |       |      |     |      |
| U |            |            |          |       |      |     |      |
| B |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| I |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| I |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
| N |            |            |          |       |      |     |      |
| U |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| G |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| L |            |            |          |       |      |     |      |
| I |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
|   |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| F |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| Y |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| M |            |            |          |       |      |     |      |
| / |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| X |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| I |            |            |          |       |      |     |      |
| M |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| N |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| G |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| F |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| / |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
|   |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| V |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| L |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| / |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
| N |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
|   |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| B |            |            |          |       |      |     |      |
| Y |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| H |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
| N |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
|   |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
|   |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
|   |            |            |          |       |      |     |      |
| G |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| F |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| M |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| I |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| L |            |            |          |       |      |     |      |
| S |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| V |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| L |            |            |          |       |      |     |      |
| U |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| P |            |            |          |       |      |     |      |
| H |            |            |          |       |      |     |      |
| O |            |            |          |       |      |     |      |
| N |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| R |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| C |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| I |            |            |          |       |      |     |      |
| V |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| V |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| L |            |            |          |       |      |     |      |
| U |            |            |          |       |      |     |      |
| A |            |            |          |       |      |     |      |
| T |            |            |          |       |      |     |      |
| E |            |            |          |       |      |     |      |
| D |            |            |          |       |      |     |      |
+---+------------+------------+----------+-------+------+-----+------+
| I | COMPONENT  | COMPONENT  | PROPOSED | TYPE  | SP   | T   | O    |
| T | TYPE, SIZE | MA         | LUB      | & NO. | EED, | YPE | THER |
| E | MAT        | NUFACTURER | RICATION | OF    | TE   | OF  | DETA |
| M | ERIAL^(1)^ |            |          |       | MP., | LO  | ILS^ |
|   |            | & MFR.     | SYSTEM & | WEAR  | ATM. | ADS | (5)^ |
| N |            | IDEN       |          | C     |      | &   |      |
| O |            | TIFICATION | AMT. OF  | YCLES | OF   | A   |      |
| . |            |            | L        | ^(2)^ | OP   | MT. |      |
|   |            |            | UBRICANT |       | ERAT |     |      |
|   |            |            |          |       | ION^ |     |      |
|   |            |            |          |       | (3)^ |     |      |
+---+------------+------------+----------+-------+------+-----+------+
|   | >          |            |          |       |      |     |      |
|   |  **NOTES** |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | > \(1\) BB |            |          |       |      |     |      |
|   | > = ball   |            |          |       |      |     |      |
|   | > bearing, |            |          |       |      |     |      |
|   | > SB =     |            |          |       |      |     |      |
|   | > sleeve   |            |          |       |      |     |      |
|   | > bearing, |            |          |       |      |     |      |
|   | > G =      |            |          |       |      |     |      |
|   | > gear, SS |            |          |       |      |     |      |
|   | > =        |            |          |       |      |     |      |
|   | > sliding  |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  surfaces, |            |          |       |      |     |      |
|   | > SEC =    |            |          |       |      |     |      |
|   | > sliding  |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | electrical |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  contacts. |            |          |       |      |     |      |
|   | > Give     |            |          |       |      |     |      |
|   | > generic  |            |          |       |      |     |      |
|   | > iden     |            |          |       |      |     |      |
|   | tification |            |          |       |      |     |      |
|   | > of       |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  materials |            |          |       |      |     |      |
|   | > used for |            |          |       |      |     |      |
|   | > the      |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | component, |            |          |       |      |     |      |
|   | > e.g.,    |            |          |       |      |     |      |
|   | > 440C     |            |          |       |      |     |      |
|   | > steel,   |            |          |       |      |     |      |
|   | > PTFE.    |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | > \(2\)    |            |          |       |      |     |      |
|   | > CUR =    |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | continuous |            |          |       |      |     |      |
|   | > unid     |            |          |       |      |     |      |
|   | irectional |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  rotation, |            |          |       |      |     |      |
|   | > CO =     |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | continuous |            |          |       |      |     |      |
|   | > os       |            |          |       |      |     |      |
|   | cillation, |            |          |       |      |     |      |
|   | > IR =     |            |          |       |      |     |      |
|   | > in       |            |          |       |      |     |      |
|   | termittent |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  rotation, |            |          |       |      |     |      |
|   | > IO =     |            |          |       |      |     |      |
|   | > in       |            |          |       |      |     |      |
|   | termittent |            |          |       |      |     |      |
|   | > os       |            |          |       |      |     |      |
|   | cillation, |            |          |       |      |     |      |
|   | > SO =     |            |          |       |      |     |      |
|   | > small    |            |          |       |      |     |      |
|   | > os       |            |          |       |      |     |      |
|   | cillation, |            |          |       |      |     |      |
|   | > (\<30°), |            |          |       |      |     |      |
|   | > LO =     |            |          |       |      |     |      |
|   | > large    |            |          |       |      |     |      |
|   | > o        |            |          |       |      |     |      |
|   | scillation |            |          |       |      |     |      |
|   | > (\>30°), |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | > CS =     |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | continuous |            |          |       |      |     |      |
|   | > sliding, |            |          |       |      |     |      |
|   | > IS =     |            |          |       |      |     |      |
|   | > in       |            |          |       |      |     |      |
|   | termittent |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  sliding.\ |            |          |       |      |     |      |
|   | > No. of   |            |          |       |      |     |      |
|   | > wear     |            |          |       |      |     |      |
|   | > cycles:  |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  A(1-102), |            |          |       |      |     |      |
|   | > B        |            |          |       |      |     |      |
|   | (102-104), |            |          |       |      |     |      |
|   | > C        |            |          |       |      |     |      |
|   | (104-106), |            |          |       |      |     |      |
|   | > D(\>106) |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | > \(3\)    |            |          |       |      |     |      |
|   | > Speed:   |            |          |       |      |     |      |
|   | > RPM =    |            |          |       |      |     |      |
|   | > r        |            |          |       |      |     |      |
|   | evs./min., |            |          |       |      |     |      |
|   | > OPM =    |            |          |       |      |     |      |
|   | > oscillat |            |          |       |      |     |      |
|   | ions/min., |            |          |       |      |     |      |
|   | > VS =     |            |          |       |      |     |      |
|   | > variable |            |          |       |      |     |      |
|   | > speed\   |            |          |       |      |     |      |
|   | > CPM =    |            |          |       |      |     |      |
|   | > cm/min.  |            |          |       |      |     |      |
|   | > (sliding |            |          |       |      |     |      |
|   | > appl     |            |          |       |      |     |      |
|   | ications)\ |            |          |       |      |     |      |
|   | > Temp. of |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | operation, |            |          |       |      |     |      |
|   | > max. &   |            |          |       |      |     |      |
|   | > min.,    |            |          |       |      |     |      |
|   | > °C\      |            |          |       |      |     |      |
|   | > A        |            |          |       |      |     |      |
|   | tmosphere: |            |          |       |      |     |      |
|   | > vacuum,  |            |          |       |      |     |      |
|   | > air,     |            |          |       |      |     |      |
|   | > gas,     |            |          |       |      |     |      |
|   | > sealed   |            |          |       |      |     |      |
|   | > or       |            |          |       |      |     |      |
|   | > unsealed |            |          |       |      |     |      |
|   | > &        |            |          |       |      |     |      |
|   | > pressure |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | > \(4\)    |            |          |       |      |     |      |
|   | > Type of  |            |          |       |      |     |      |
|   | > loads: A |            |          |       |      |     |      |
|   | > = axial, |            |          |       |      |     |      |
|   | > R =      |            |          |       |      |     |      |
|   | > radial,  |            |          |       |      |     |      |
|   | > T =      |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | tangential |            |          |       |      |     |      |
|   | > (gear    |            |          |       |      |     |      |
|   | > load).   |            |          |       |      |     |      |
|   | > Give     |            |          |       |      |     |      |
|   | > amount   |            |          |       |      |     |      |
|   | > of load. |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   | > \(5\) If |            |          |       |      |     |      |
|   | > BB, give |            |          |       |      |     |      |
|   | > type and |            |          |       |      |     |      |
|   | > material |            |          |       |      |     |      |
|   | > of ball  |            |          |       |      |     |      |
|   | > cage and |            |          |       |      |     |      |
|   | > number   |            |          |       |      |     |      |
|   | > of       |            |          |       |      |     |      |
|   | > shields  |            |          |       |      |     |      |
|   | > and      |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  specified |            |          |       |      |     |      |
|   | > ball     |            |          |       |      |     |      |
|   | > groove   |            |          |       |      |     |      |
|   | > and ball |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  finishes. |            |          |       |      |     |      |
|   | > If G,    |            |          |       |      |     |      |
|   | > give     |            |          |       |      |     |      |
|   | > surface  |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  treatment |            |          |       |      |     |      |
|   | > and      |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  hardness. |            |          |       |      |     |      |
|   | > If SB,   |            |          |       |      |     |      |
|   | > give     |            |          |       |      |     |      |
|   | > dia. of  |            |          |       |      |     |      |
|   | > bore and |            |          |       |      |     |      |
|   | > width.   |            |          |       |      |     |      |
|   | > If       |            |          |       |      |     |      |
|   | > torque   |            |          |       |      |     |      |
|   | >          |            |          |       |      |     |      |
|   |  available |            |          |       |      |     |      |
|   | > is       |            |          |       |      |     |      |
|   | > limited, |            |          |       |      |     |      |
|   | > give     |            |          |       |      |     |      |
|   | > approx.  |            |          |       |      |     |      |
|   | > value.   |            |          |       |      |     |      |
+---+------------+------------+----------+-------+------+-----+------+
|   |            |            |          |       |      |     |      |
+---+------------+------------+----------+-------+------+-----+------+

GSFC 18-59C 3/78

[]{#__RefHeading___Toc75054504 .anchor}Figure 7‑5. Lubrication Usage
List

+---+-----------+----------+---------+---------------+----------------+
| M |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| E |           |          |         |               |                |
| R |           |          |         |               |                |
| I |           |          |         |               |                |
| A |           |          |         |               |                |
| L |           |          |         |               |                |
| S |           |          |         |               |                |
| P |           |          |         |               |                |
| R |           |          |         |               |                |
| O |           |          |         |               |                |
| C |           |          |         |               |                |
| E |           |          |         |               |                |
| S |           |          |         |               |                |
| S |           |          |         |               |                |
| U |           |          |         |               |                |
| T |           |          |         |               |                |
| I |           |          |         |               |                |
| L |           |          |         |               |                |
| I |           |          |         |               |                |
| Z |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| I |           |          |         |               |                |
| O |           |          |         |               |                |
| N |           |          |         |               |                |
| L |           |          |         |               |                |
| I |           |          |         |               |                |
| S |           |          |         |               |                |
| T |           |          |         |               |                |
|   |           |          |         |               |                |
| S |           |          |         |               |                |
| P |           |          |         |               |                |
| A |           |          |         |               |                |
| C |           |          |         |               |                |
| E |           |          |         |               |                |
| C |           |          |         |               |                |
| R |           |          |         |               |                |
| A |           |          |         |               |                |
| F |           |          |         |               |                |
| T |           |          |         |               |                |
| S |           |          |         |               |                |
| Y |           |          |         |               |                |
| S |           |          |         |               |                |
| T |           |          |         |               |                |
| E |           |          |         |               |                |
| M |           |          |         |               |                |
| / |           |          |         |               |                |
| E |           |          |         |               |                |
| X |           |          |         |               |                |
| P |           |          |         |               |                |
| E |           |          |         |               |                |
| R |           |          |         |               |                |
| I |           |          |         |               |                |
| M |           |          |         |               |                |
| E |           |          |         |               |                |
| N |           |          |         |               |                |
| T |           |          |         |               |                |
| G |           |          |         |               |                |
| S |           |          |         |               |                |
| F |           |          |         |               |                |
| C |           |          |         |               |                |
| T |           |          |         |               |                |
| / |           |          |         |               |                |
| O |           |          |         |               |                |
|   |           |          |         |               |                |
| D |           |          |         |               |                |
| E |           |          |         |               |                |
| V |           |          |         |               |                |
| E |           |          |         |               |                |
| L |           |          |         |               |                |
| O |           |          |         |               |                |
| P |           |          |         |               |                |
| E |           |          |         |               |                |
| R |           |          |         |               |                |
| / |           |          |         |               |                |
| C |           |          |         |               |                |
| O |           |          |         |               |                |
| N |           |          |         |               |                |
| T |           |          |         |               |                |
| R |           |          |         |               |                |
| A |           |          |         |               |                |
| C |           |          |         |               |                |
| T |           |          |         |               |                |
| O |           |          |         |               |                |
| R |           |          |         |               |                |
| A |           |          |         |               |                |
| D |           |          |         |               |                |
| D |           |          |         |               |                |
| R |           |          |         |               |                |
| E |           |          |         |               |                |
| S |           |          |         |               |                |
| S |           |          |         |               |                |
|   |           |          |         |               |                |
| P |           |          |         |               |                |
| R |           |          |         |               |                |
| E |           |          |         |               |                |
| P |           |          |         |               |                |
| A |           |          |         |               |                |
| R |           |          |         |               |                |
| E |           |          |         |               |                |
| D |           |          |         |               |                |
| B |           |          |         |               |                |
| Y |           |          |         |               |                |
| P |           |          |         |               |                |
| H |           |          |         |               |                |
| O |           |          |         |               |                |
| N |           |          |         |               |                |
| E |           |          |         |               |                |
| D |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| E |           |          |         |               |                |
| P |           |          |         |               |                |
| R |           |          |         |               |                |
| E |           |          |         |               |                |
| P |           |          |         |               |                |
| A |           |          |         |               |                |
| R |           |          |         |               |                |
| E |           |          |         |               |                |
| D |           |          |         |               |                |
|   |           |          |         |               |                |
| G |           |          |         |               |                |
| S |           |          |         |               |                |
| F |           |          |         |               |                |
| C |           |          |         |               |                |
| M |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| E |           |          |         |               |                |
| R |           |          |         |               |                |
| I |           |          |         |               |                |
| A |           |          |         |               |                |
| L |           |          |         |               |                |
| S |           |          |         |               |                |
| E |           |          |         |               |                |
| V |           |          |         |               |                |
| A |           |          |         |               |                |
| L |           |          |         |               |                |
| U |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| O |           |          |         |               |                |
| R |           |          |         |               |                |
| P |           |          |         |               |                |
| H |           |          |         |               |                |
| O |           |          |         |               |                |
| N |           |          |         |               |                |
| E |           |          |         |               |                |
| D |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| E |           |          |         |               |                |
| R |           |          |         |               |                |
| E |           |          |         |               |                |
| C |           |          |         |               |                |
| E |           |          |         |               |                |
| I |           |          |         |               |                |
| V |           |          |         |               |                |
| E |           |          |         |               |                |
| D |           |          |         |               |                |
| D |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| E |           |          |         |               |                |
| E |           |          |         |               |                |
| V |           |          |         |               |                |
| A |           |          |         |               |                |
| L |           |          |         |               |                |
| U |           |          |         |               |                |
| A |           |          |         |               |                |
| T |           |          |         |               |                |
| E |           |          |         |               |                |
| D |           |          |         |               |                |
+---+-----------+----------+---------+---------------+----------------+
| I | PROCESS   | CO       | MIL.,   | DESCRIPTION   | S              |
| T | TYPE^(1)^ | NTRACTOR | ASTM.,  | OF MAT'L      | PACECRAFT/EXP. |
| E |           | SPEC.    | FED.    | P             | AP             |
| M |           | NO.^(2)^ |         | ROCESSED^(3)^ | PLICATION^(4)^ |
|   |           |          | OR      |               |                |
| N |           |          | OTHER   |               |                |
| O |           |          | SPEC.   |               |                |
| . |           |          | NO.     |               |                |
+---+-----------+----------+---------+---------------+----------------+
|   |           |          |         |               |                |
+---+-----------+----------+---------+---------------+----------------+
|   | >         |          |         |               |                |
|   | **NOTES** |          |         |               |                |
|   | >         |          |         |               |                |
|   | > \(1\)   |          |         |               |                |
|   | > Give    |          |         |               |                |
|   | > generic |          |         |               |                |
|   | > name of |          |         |               |                |
|   | >         |          |         |               |                |
|   |  process, |          |         |               |                |
|   | > e.g.,   |          |         |               |                |
|   | >         |          |         |               |                |
|   | anodizing |          |         |               |                |
|   | >         |          |         |               |                |
|   | (sulfuric |          |         |               |                |
|   | > acid).  |          |         |               |                |
|   | >         |          |         |               |                |
|   | > \(2\)   |          |         |               |                |
|   | > If      |          |         |               |                |
|   | > process |          |         |               |                |
|   | > if      |          |         |               |                |
|   | > pro     |          |         |               |                |
|   | prietary, |          |         |               |                |
|   | > please  |          |         |               |                |
|   | > state   |          |         |               |                |
|   | > so.     |          |         |               |                |
|   | >         |          |         |               |                |
|   | > \(3\)   |          |         |               |                |
|   | >         |          |         |               |                |
|   |  Identify |          |         |               |                |
|   | > the     |          |         |               |                |
|   | > type    |          |         |               |                |
|   | > and     |          |         |               |                |
|   | >         |          |         |               |                |
|   | condition |          |         |               |                |
|   | > of the  |          |         |               |                |
|   | >         |          |         |               |                |
|   |  material |          |         |               |                |
|   | >         |          |         |               |                |
|   | subjected |          |         |               |                |
|   | > to the  |          |         |               |                |
|   | >         |          |         |               |                |
|   | process.\ |          |         |               |                |
|   | > E.g.,   |          |         |               |                |
|   | > 6061-T6 |          |         |               |                |
|   | >         |          |         |               |                |
|   | > \(4\)   |          |         |               |                |
|   | >         |          |         |               |                |
|   |  Identify |          |         |               |                |
|   | > the     |          |         |               |                |
|   | >         |          |         |               |                |
|   | component |          |         |               |                |
|   | > or      |          |         |               |                |
|   | >         |          |         |               |                |
|   | structure |          |         |               |                |
|   | > of      |          |         |               |                |
|   | > which   |          |         |               |                |
|   | > the     |          |         |               |                |
|   | >         |          |         |               |                |
|   | materials |          |         |               |                |
|   | > are     |          |         |               |                |
|   | > being   |          |         |               |                |
|   | > pr      |          |         |               |                |
|   | ocessed.\ |          |         |               |                |
|   | > E.g.,   |          |         |               |                |
|   | > Antenna |          |         |               |                |
|   | > dish    |          |         |               |                |
+---+-----------+----------+---------+---------------+----------------+
|   |           |          |         |               |                |
+---+-----------+----------+---------+---------------+----------------+

GSFC 18-59D 3/78

[]{#__RefHeading___Toc75054505 .anchor}Figure 7‑6. Materials Process
Utilization List

# RESERVED

# DESIGN VERIFICATION REQUIREMENTS 

## GENERAL REQUIREMENTS

A verification program shall be conducted to ensure that the systems
meet the specified mission requirements. The program shall consist of
functional demonstrations, analytical investigations, physical
measurements and tests that simulate all expected environments. Adequate
verification documentation shall be provided including a verification
plan and matrix, environmental test matrix and verification procedures.

The Verification Program begins with functional testing of assemblies.
It continues through functional and environmental testing supported by
appropriate analysis, at the component, subsystem and instrument levels
of assembly. The program concludes with end-to-end testing of the entire
operational system, including the instrument and the appropriate Ground
Data System elements.

The General Environmental Verification Specification (GEVS) for ELV
Payloads, Subsystems, and Components shall be used as a baseline guide
for developing the verification program. For a copy of the GEVS
document, use the following hyperlink \-\--
<http://arioch.gsfc.nasa.gov/302/verifhp.htm>. Alternative methods are
acceptable provided that the net result demonstrates compliance with the
intent of the requirements.

## DOCUMENTATION REQUIREMENTS

### System Performance Verification Plan

A System Performance Verification Plan shall be prepared and implemented
(reference GEVS Section 2.1 and the CDRL). The plan shall define the
tasks and methods required to verify the ability of the system to meet
each specified mission requirement (structural, thermal, optical,
electrical, guidance/control, RF/telemetry, science, mission
operational, etc.), including records documenting compliance.
Limitations in the ability to verify any performance requirement shall
be addressed, including the addition of supplemental tests and/or
analyses that will be performed and a risk assessment of the inability
to fully verify the requirement.

The plan shall address how compliance with each specification
requirement will be verified. If verification relies on the results of
measurements and/or analyses performed at lower (or other) levels of
assembly, this dependence shall be described.

For each analysis activity, the plan shall include objectives, a
description of the mathematical model, assumptions on which the models
will be based, required output, criteria for assessing the acceptability
of the results, the interaction with related test activity, if any, and
requirements for reports. Analysis results shall take into account
tolerance build-ups in the parameters being used.

#### System Performance Verification Matrix

Documentation to demonstrate compliance with each system performance
requirement shall be provided. A matrix, or equivalent system, shall be
prepared and maintained that shows the flow-down of each performance
requirement and the verification process. The matrix shall be iterated
as verification is completed, kept current, and the status made
available upon request. The matrix shall be included in the system
review data packages showing the current verification status.

#### Performance Verification Procedures

For each performance verification test activity conducted at the
component, subsystem, and instrument levels (or other appropriate
levels) of assembly, procedures shall be prepared for verifying
compliance with each system performance requirement. These procedures
shall identify the verification article configuration and provide
detailed instructions for accomplishing and documenting the verification
activity. As-run copies of these procedures shall be archived for
reference via a user-friendly retrieval process.

Verification test procedures shall contain details such as
instrumentation monitoring, facility control sequences, test article
functions, test parameters, pass/fail criteria, quality control
checkpoints, data collection, and reporting requirements. The procedures
shall also address safety and contamination control provisions.

#### Performance Verification Reports

Upon completion of each system performance verification activity, a
report shall be prepared to summarize the findings and results. This
report may be attached to the applicable as-run procedures or archived
as a separate document. The combined matrix, as-run procedure records,
and summary reports shall be developed and maintained \"real-time\"
throughout the program; thereby demonstrating compliance with the
applicable system performance requirements prior to delivery of
hardware/ software to the next higher level of assembly.

### Environmental Verification Plan

An Environmental Verification Plan (EVP) shall be prepared as part of
the System Performance Verification Plan, or as a separate document, to
prescribe the tests and analyses which will collectively demonstrate
that the hardware and software comply with the environmental
verification requirements. The EVP shall provide the overall approach to
accomplishing the environmental verification program. For each test, it
shall include the level of assembly, the configuration of the item,
objectives, facilities, instrumentation, safety considerations,
contamination control, test phases and profiles, necessary functional
operations, personnel responsibilities, and requirement for procedures
and reports. It shall also define a rationale for retest determination
that does not invalidate previous verification activities. When
appropriate, the interaction of the test and analysis activity shall be
described.

Limitations in the environmental verification program that preclude the
verification by test of any system requirement shall be documented.
Alternative tests and analyses shall be evaluated and implemented as
appropriate, and an assessment of the project risk shall be included in
the System Performance Verification Plan.

The preliminary plan shall provide sufficient verification philosophy
and detail to allow assessment of the program. For example, for the
environmental test portion of the verification, it is not sufficient to
state that the GEVS requirements will be met. A program philosophy must
be included. Examples of program philosophy are:

-   All components shall be subjected to random vibration.

-   Random vibration shall be performed at the subsystem level of
    assembly rather than at the component level.

-   All instruments shall be subjected to acoustics tests and 3-axis
    sine and random vibration.

-   All components shall be subjected to EMC tests.

-   All flight hardware shall see 8-thermal-vacuum cycles prior to
    integration on the spacecraft.

#### Environmental Verification Specification

As part of the System Performance Verification Plan, or as a separate
document, an environmental verification specification shall be prepared
that defines the specific environmental parameters that each system
element is subjected to either by test or analysis in order to
demonstrate its ability to meet the mission performance requirements.
Such things as payload peculiarities and interaction with the launch
vehicle shall be taken into account.

#### Environmental Test Matrix

As an adjunct to the system Environmental Verification Plan, a matrix,
or equivalent system, shall be prepared and maintained that identifies
all environmental tests that will be performed on each component,
subsystem, and instrument clearly showing each environmental exposure
and test article level of assembly. For an example of an environmental
test matrix, refer to GEVS Figure 2.1-1. The purpose is to provide a
ready reference to the contents of the environmental test program in
order to prevent the deletion of a portion thereof without an
alternative means of accomplishing the objectives. All flight hardware,
spares and prototypes (when appropriate) shall be included in the
matrix. The matrix shall be iterated as performance is completed, kept
current, and the status made available upon request. The matrix shall be
prepared in conjunction with the initial environmental verification plan
and shall be updated as the project matures. This matrix may be combined
with the Performance Verification Matrix on a common database. The
matrix shall be included in the system review data packages showing the
current status.

## ELECTRICAL FUNCTIONAL TEST REQUIREMENTS

### Electrical Interface Tests

As a part of the integration of a component or subsystem into the next
higher level of assembly, electrical tests (reference GEVS Section
2.3.1) shall be performed to verify the interface configuration (power,
grounds, commands, telemetry, signals, timing, etc,). Prior to mating
with other hardware, electrical harnessing shall be tested to verify the
wire routing, isolation, impedance, and overall workmanship. The
following parameters shall be verified as a minimum:

-   Accuracy (signals on correct pins and nowhere else)

-   Inputs and outputs (unloaded and loaded)

-   Specified range (high/low extremes as well as nominal)

-   Range impacts (how range extremes of one signal affect related
    signals)

### Aliveness Tests

An aliveness test may be performed to verify that the instrument and its
major components are functioning.

### Comprehensive Performance Tests (CPTs)

Appropriate CPTs shall be conducted at the subsystem and instrument
levels of assembly (reference GEVS Section 2.3.2). The CPT shall be a
detailed demonstration that the hardware and software meet their
performance requirements within allowable tolerances. The CPT shall
demonstrate the operation of redundant circuitry and satisfactory
performance in all operational modes. CPTs shall demonstrate that, with
the application of known stimuli and appropriate inputs, the test
article will produce the expected responses and outputs within
acceptable limits. The initial CPT shall serve as a baseline against
which the results of all later CPT's can be readily compared. CPT's
shall be identified in the System Performance Verification Plan.
Specific times when CPTs will be performed shall be described in the
Verification Plans.

### Limited Performance Tests (LPTs)

Appropriate LPTs shall be conducted at the subsystem and instrument
levels of assembly when CPTs are not warranted to demonstrate that the
functional capability has not been degraded (reference GEVS Section
2.3.3). The LPT shall be a demonstration that the hardware and software
meet their performance requirements within allowable tolerances. The LPT
shall demonstrate the operation of redundant circuitry and satisfactory
performance in selected operational modes. LPTs shall demonstrate that,
with the application of known stimuli and appropriate inputs, the test
article will produce the expected responses and outputs within
acceptable limits. The initial LPT shall serve as a baseline against
which the results of all later LPTs can be readily compared. Specific
times when LPTs will be performed shall be described in the Verification
Plans.

### Support to End-to-End Performance Tests 

The Contractor shall provide support to an end-to-end compatibility test
which will be performed to demonstrate the ground system capability to
communicate with the Observatory (up-link and down-link) via the ground
to space network (reference GEVS Section 2.8). Simulated normal orbital
mission scenarios encompassing launch, systems turn-on, housekeeping,
command/control, and stabilization/pointing will be demonstrated,
including the collecting, processing, and archiving of science data.
Observatory immunity to erroneous commands, autonomous safe-hold, and
simulated anomaly recovery operations will also be demonstrated.

### Performance Operating Time and Failure-Free Performance Testing

At the conclusion of the performance verification program, the OLI shall
have demonstrated 1000 hours of operating time and demonstrated
failure-free performance testing for a minimum of the final 300 hours of
operation.

## Environmental Testing REQUIREMENTS

Compliance with the specified structural and mechanical requirements
shall be demonstrated through a series of interdependent test and
analysis activities (reference GEVS Section 2.4). These demonstrations
shall verify design and specified factors of safety as well as ensure
instrument interface compatibility, acceptable workmanship, and material
integrity. Safety requirements shall be accomplished in conjunction with
these demonstrations.

The design shall be sufficiently modularized to permit realistic
environmental exposures at the component and subsystem level. Each
subsystem shall be verified for each of the applicable requirements
identified. It is the Contractor's responsibility to document a
meaningful set of design verification activities that best demonstrates
compliance with the systems performance requirements.

When planning the tests and analyses, the Contractor shall consider all
expected environments, including the following:

-   Structural loads (reference GEVS Section 2.4.1)

-   Thermal balance (reference GEVS Section 2.6.3)

-   Mass properties (reference GEVS Section 2.4.7)

-   Mechanical mechanism functions (reference GEVS Section 2.4.5)

-   Vibration (acoustics, 3-axis sine sweep and random) (reference GEVS
    Sections 2.4.2, 2.4.3)

-   Mechanical shock (self induced, externally induced) (reference GEVS
    Section 2.4.4)

-   Thermal vacuum (reference GEVS Section 2.6)

-   Electromagnetic Compatibility (EMC) Requirements (reference GEVS
    Section 2.5)

# WORKMANSHIP STANDARDS

## GENERAL REQUIREMENTS

The Contractor shall plan and implement an Electronic Packaging and
Processes Program to assure that all electronic packaging technologies,
processes, and workmanship activities selected and applied meet mission
objectives for quality and reliability.

## APPLICABLE DOCUMENTS

The NASA preferred standards identified in the NASA technical standards
program in the NASA Online Directives Information System (NODIS) shall
be used. For copies of referenced documents, use the following hyperlink
\-\-- <http://standards.nasa.gov/>

-   [Conformal Coating and Staking:]{.underline} NASA-STD-8739.1,
    "Workmanship Standard for Staking and Conformal Coating of Printed
    Wiring Boards and Electronic Assemblies".

-   [Soldering -- Flight, Surface Mount Technology:]{.underline}
    NASA-STD-8739.2, "Surface Mount Technology".

-   [Soldering -- Flight, Manual (hand):]{.underline} NASA-STD-8739.3,
    "Soldered Electrical Connections".

-   [Soldering -- Ground Systems:]{.underline} Association Connecting
    Electronics Industries (IPC)/Electronics Industry Alliance (EIA)
    J-STD-001C, "Requirements for Soldered Electrical and Electronic
    Assemblies".

-   [Electronic Assemblies -- Ground Systems:]{.underline} IPC-A-610C,
    "Acceptability of Electronic Assemblies".

-   [Crimping, Wiring, and Harnessing:]{.underline} NASA-STD-8739.4,
    "Crimping, Interconnecting Cables, Harnesses, and Wiring".

-   [Fiber Optics:]{.underline} NASA-STD-8739.5, "Fiber Optic
    Terminations, Cable Assemblies, and Installation".

-   [ESD Control:]{.underline} ANSI/ESD S20.20, "Protection of
    Electrical and Electronic Parts, Assemblies and Equipment"
    (excluding electrically initiated explosive devices).

```{=html}
<!-- -->
```
-   [Printed Wiring Board (PWB) Design:]{.underline}

    -   IPC-2221, "Generic Standard on Printed Board Design".

    -   IPC-2222, "Sectional Design Standard for Rigid Organic Printed
        Boards".

    -   IPC-2223, "Sectional Design Standard for Flexible Printed
        Boards".

```{=html}
<!-- -->
```
-   PWB Manufacture:

    -   IPC A-600F, "Acceptability of Printed Boards".

    -   IPC-6011, "Generic Performance Specification for Printed
        Boards".

    -   IPC-6012, "Qualification and Performance Specification for Rigid
        Printed Boards"

        -   Flight Applications -- Supplemented with: GSFC S312-P-003,
            Procurement Specification for Rigid Printed Boards for Space
            Applications and Other High Reliability Uses (copy in
            Appendix D)

    -   IPC-6013, "Qualification and Performance Specification for
        Flexible Printed Boards".

Alternate workmanship standards may be used when approved by the GSFC
LDCM Project. The Contractor shall submit the alternate standard
(identifying the differences between the alternate standard and the
required standard) for GSFC LDCM Project approval prior to use.

## DESIGN

### Printed Wiring Boards (PWB)

The PWB manufacturing and acceptance requirements identified in this
chapter are based on using PWBs designed in accordance with the PWB
design standards referenced above. Space flight PWB designs shall not
include features that prevent the finished boards from complying with
the Class 3 requirements of the appropriate manufacturing standard
(e.g., specified plating thickness, internal annular ring dimensions,
etc.).

### Ground Data Systems (GDS)

GDS assemblies, that interface directly with space flight hardware,
shall be designed and fabricated using space flight parts, materials,
and processes for any portion of the assemblies (connectors, test
cables, etc.) that:

-   mate with the flight hardware

-   will reside with the space flight hardware in environmental chambers
    or other test facilities that simulate a space flight environment

## WORKMANSHIP REQUIREMENTS

### Training and Certification

All personnel working on flight hardware (and applicable GDS) shall be
certified as having completed the required training, appropriate to
their involvement, as defined in the above standards. This includes, but
is not limited to, the aforementioned workmanship and ESD standards.

### Flight Workmanship

PWBs shall be manufactured in accordance with the Class 3 requirements
in the above referenced IPC PWB manufacturing standards and
GSFC/S312-P-003, "Procurement Specification for Rigid Printed Boards for
Space Applications and Other High Reliability Uses". PWB test coupons
shall be provided to the GSFC Materials Engineering Branch (MEB) or a
GSFC/MEB approved laboratory for evaluation in accordance with contract
requirements. GSFC approval shall be obtained prior to population of
flight PWBs. Test coupons and test reports evaluated by a GSFC/MEB
approved laboratory are not required for delivery to GSFC/MEB. However,
the coupons/reports shall be retained and included as part of the
documentation/data deliverables package to the LDCM project.

### GDS (non-flight) Workmanship

PWBs shall be manufactured in accordance with the Class 2 requirements
in the above referenced IPC PWB manufacturing standards. Assemblies
shall be fabricated using the Class 2 requirements of J-STD-001C,
IPC-A-610C, and ANSI/ESD S20.20. If any conflicts between J-STD-001C and
IPC-A-610C are encountered, the requirements in J-STD-001C shall take
precedence.

## ESD REQUIREMENTS

The Contractor shall document and implement an ESD Control Program,
compliant with ANSI/ESD S20.20, Protection of Electrical and Electronic
Parts, Assemblies and Equipment (excluding electrically initiated
explosive devices. The program shall protect the most sensitive parts
involved in the project and ensure that all manufacturing, inspection,
testing, and other processes will not compromise mission objectives for
quality and reliability due to ESD events. At a minimum, the ESD Control
Program shall address training, protected work area procedures and
verification schedules, packaging, facility maintenance, handling,
storage, and shipping.

All personnel who manufacture, inspect, test, otherwise process
electronic hardware, or require unescorted access into ESD protected
areas shall be certified as having completed the required training,
appropriate to their involvement, as defined in ANSI/ESD S20 prior to
handling any electronic hardware.

Electronic hardware shall be manufactured, inspected, tested, or
otherwise processed only at designated ESD protective work areas. These
work areas shall be verified on a regular schedule as identified in the
ESD Control Program.

Electronic hardware shall be properly packaged in ESD protective
packaging at all times when not actively being manufactured, inspected,
tested, or otherwise processed. Materials selected for packaging or
protecting ESD sensitive devices shall not leach chemicals, leave
residues, or otherwise contaminate parts or assemblies.

## NEW/ADVANCED PACKAGING TECHNOLOGIES

New and/or advanced packaging technologies (multi-chip modules (MCMs),
stacked memories, chip on board, etc.) that have not previously been
used in space flight applications shall be reviewed and approved through
the Parts Control Board (PCB) as defined in Chapter 6. When appropriate,
a detailed Technology Validation Assessment Plan (TVAP) may be developed
for each new technology. A TVAP identifies the evaluations and data
necessary for acceptance of the new/advanced technology for reliable use
and conformance to project requirements.

New/advanced technologies will be part of the Parts Identification List
(PIL) and Project Approved Parts List (PAPL) defined in Section 6.3 of
this document.

# RISK MANAGEMENT REQUIREMENTS

## GENERAL REQUIREMENTS

The Contractor shall plan and implement a Continuous Risk Management
(CRM) program applicable to the development of all software and hardware
products and processes (flight and ground.

The Contractor shall:

a.  Identify, document, evaluate, classify, and prioritize reliability
    risks before they become problems

b.  Develop and implement risk mitigation strategies, actions, and tasks
    and assign appropriate resources

c.  Track risk being mitigated; capture risk attributes and mitigation
    information by collecting data; establish performance metrics; and
    examine trends, deviations, and anomalies

d.  Control risks by performing: risk close-out, re-planning,
    contingency planning, or continued tracking and execution of the
    current plan

e.  Communicate and document (via the risk recording, reporting, and
    monitoring system) risk information to ensure it is conveyed between
    all levels of the project

f.  Report on outstanding risk items at all management and design
    reviews.

## RISK MANAGEMENT PLAN

The Contractor shall prepare a Risk Management Plan, in accordance with
the CDRL, applicable to the system level for which they are responsible.
The plan shall include risks associated with hardware (technical
challenges, new technology qualification, etc.), software, COTS, system
safety, performance, and programmatic risks (cost and schedule). The
plan shall identify which tools and techniques will be used to manage
risks. The risk areas that are identified shall be addressed at peer
reviews (component, subsystem) and technical reviews (instrument).
Although not all risks will be fully mitigated, all risks shall be
addressed with mitigation and acceptance strategies agreed upon at
appropriate reviews.

# CONTAMINATION CONTROL REQUIREMENTS

## GENERAL REQUIREMENTS

The Contractor shall plan and implement a contamination control program
for LDCM hardware. Specific cleanliness requirements shall be
established and the approaches to meet the requirements shall be
delineated in a Contamination Control Plan (CCP) deliverable to the GSFC
CO for concurrence.

Contamination includes all materials of molecular and particulate nature
whose presence degrades hardware performance. The source of the
contaminant materials may be the hardware itself, the test facilities,
and the environments to which the hardware is exposed.

## CONTAMINATION CONTROL PLAN

A CCP shall be prepared that describes the procedures that will be
followed to control contamination. The CCP shall define a contamination
allowance for performance degradation of contamination sensitive
hardware such that, even in the degraded state, the hardware will meet
its mission objectives. The CCP shall establish the implementation and
describe the methods that will be used to measure and maintain the
levels of cleanliness required during each of the various phases of the
hardware\'s lifetime. The contamination potential of material and
equipment used in cleaning, handling, packaging, tent enclosures,
shipping containers, bagging (e.g., anti-static film materials), and
purging shall be described in detail for each subsystem or component at
each phase of assembly, integration, test, and launch. In general, all
mission hardware should be compatible with the most
contamination-sensitive components.

## MATERIAL OUTGASSING

All materials shall be screened in accordance with NASA Reference
Publication 1124, Outgassing Data for Selecting Spacecraft Materials.
Individual material outgassing data shall be established based on each
component\'s operating conditions. Established material outgassing data
shall be verified and shall be provided to the GSFC LDCM Project for
review.

## THERMAL VACUUM BAKEOUT

Thermal vacuum bakeouts of all hardware shall be performed as required
to protect contamination-sensitive components. The parameters of such
bakeouts (e.g., temperature, duration, outgassing requirements, and
pressure) must be individualized depending on materials used, the
fabrication environment, and the established contamination allowance.
Thermal vacuum bakeout results shall be verified and shall be provided
to the GSFC LDCM Project for review.

A quartz crystal microbalance (QCM), or temperature controlled quartz
crystal microbalance (TQCM), and cold finger shall be incorporated
during all thermal vacuum bakeouts at the instrument level. These
devices shall provide additional information to enable a determination
of the duration and effectiveness of the thermal vacuum bakeout as well
as compliance with the CCP.

A.  []{#__RefHeading___Toc100548489 .anchor}REFERENCE DOCUMENTS LIST

  ---------------------- ----------------------------------------------------
  **DOCUMENT**           **DOCUMENT TITLE**

  AFSPC 91-710           Range Safety User Requirements Manual

  ANSI/ESD S20.20        ESD Association Standard for the Development of an
                         Electrostatic Discharge Control Program for
                         Protection of Electrical and Electronic Parts,
                         Assemblies and Equipment (excluding electrically
                         initiated explosive devices)

  ANSI/IPC-D-275         Design Standard for Rigid Printed Boards and Rigid
                         Printed Board Assemblies

  ANSI/ISO/ASQ           American National Standard Quality Management System
  Q9001-2000             Requirements

  ANSI/ISO/ASQC          American National Standard Quality Systems - Model
  Q9001-1994             for Quality Assurance in Design, Development,
                         Production, Installation, and Servicing

  ANSI/ISO/ASQC-Q10013   Guidelines for Developing Quality Manuals

  ANSI/ISO-17025         General Requirements for the Competence of Testing
                         and Calibration Laboratories

  ASTM E-595             Total Mass Loss (TML) and Collected Volatile
                         Condensable Materials (CVCM) from Outgassing in a
                         Vacuum Environment

  GEVS                   General Environmental Verification Specification for
                         STS & ELV Payloads, Subsystems, and Components, rev
                         A, dated June 1996

  GSFC PPL-21            GSFC Preferred Parts List

  EEE-INST-002           Instructions for EEE Parts Selection, Screening,
                         Qualification, and Derating

  GSFC S312-P-003        Procurement Specification for Rigid Printed Boards
                         for Space Applications and Other High Reliability
                         Uses

  IEEE STD 730           IEEE Standard for Software Quality Assurance Plans

  IPC-A-600              Acceptability of Printed Wiring Boards

  IPC-A-610C             Acceptability of Electronic Assemblies

  IPC/EIA J-STD-001C     Requirements for Soldered Electrical and Electronic
                         Assemblies

  IPC-2221               Generic Standard on Printed Board Design

  IPC-2222               Sectional Design Standard for Rigid Organic Printed
                         Boards

  IPC-2223               Sectional Design Standard for Flexible Printed
                         Boards

  IPC-6011               Generic Performance Specifications for Printed
                         Boards

  IPC-6012               Qualification and Performance Specification for
                         Rigid Printed Boards

  IPC-6013               Qualification and Performance Specification for
                         Flexible Printed Boards

  JSC 26943              Guidelines for the Preparation of Payload Flight
                         Safety Data Packages and Hazard Reports

  KHB 1700.7C            Space Transportation System Payload Ground Safety
                         Handbook

  KHB 1710.2D            Kennedy Space Center Safety Practices Handbook

  MIL-HDBK-217           Reliability Prediction of Electronic Equipment

  MIL-STD 1629A          Procedures for Performing a Failure Mode Effects and
                         Criticality Analysis

  MIL-STD-756B           Reliability Modeling and Prediction

  MSFC CR 5320.9         Payload and Experiment Failure Mode Effects Analysis
                         and Critical Items List Ground Rules

  MSFC-HDBK-527          Material Selection List for Space Hardware Systems

  MSFC-SPEC-522          Design Criteria for Controlling Stress Corrosion
                         Cracking

  NASA RP 1124           Outgassing Data for Selecting Spacecraft Materials

  NASA RP-1161           Evaluation of Multi-layer Printed Wiring Boards by
                         Metallographic Techniques

  NASA-STD-6001          Flammability, Odor, Off-Gassing and Compatibility
                         Requirement and Test Procedures for Materials in
                         Environments that Support Combustion

  NASA-STD-8719.8        Expendable Launch Vehicle Payload Safety Review
                         Process Standard

  NASA-STD-8719.13A      NASA Software Safety Standard

  NASA-STD-8729.1        Planning, Developing, and Managing an Effective
                         Reliability and Maintainability (R&M) Program

  NASA-STD-8739.1        Workmanship Standard for Staking and Conformal
                         Coating of Printed Wiring Boards and Electronic
                         Assemblies

  NASA-STD-8739.2        Workmanship Standard for Surface Mount Technology

  NASA-STD-8739.3        Workmanship Standard for Soldered Electrical
                         Connections

  NASA-STD-8739.4        Workmanship Standard for Crimping, Interconnecting
                         Cables, Harnesses and Wiring

  NASA-STD-8739.5        Workmanship Standard for Fiber Optic Terminations,
                         Cable Assemblies and Installation

  NHB 1700.7             Safety Policy and Requirements for Payloads using
                         the Space Transportation System

  NPD 8700.1             NASA Policy for Safety and Mission Success

  NPD 8710.3             NASA Policy for Limiting Orbital Debris Generation

  NPD 8720.1             NASA Reliability and Maintainability (R&M) Program
                         Policy

  NPG 7120.5             Program and Project Management Process and
                         Requirements

  NPSL                   NASA Parts Selection List

  NSS 1740.13            Software Safety Standard

  NSS 1740.14            Guidelines and Assessment Procedures for Limiting
                         Orbital Debris

  NUREG-0492             Fault Tree Handbook

  RADC-TR-85-229         Reliability Predictions for Spacecraft

  S-311-M-70             Specification for Destructive Physical Analysis

  541-PG-8072.1.2        Goddard Space Flight Center Fastener Integrity
                         Requirements (formerly GSFC S-313-100)
  ---------------------- ----------------------------------------------------