-_SOW.pdf

Effective Date: 05/11/2018 Expiration Date: 05/11/2023

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400-FORM-0002 (4/16/2014)

LANDER-PROP-SOW-0003, Revision - EUROPA Lander Propulsion, Code 597

Engine Development Statement of Work

EAR ECCN - [9E515]

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National Aeronautics and Space Administration

Goddard Space Flight Center Greenbelt, Maryland https://ipdtdms.gsfc.nasa.gov/

Engine SOW LANDER-PROP-SOW-0003, Revision -ii Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

Engine Statement of Work Signature/Approval Page

Revision - Prepared by:

Eric Cardiff

Approved by:

Eric Cardiff

*** Electronic signatures are available on-line at:

https://ipdtdms.gsfc.nasa.gov*** https://ipdtdms.gsfc.nasa.gov/ iii Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

Preface This document is a Europa Clipper Propulsion project signature-controlled document. Changes to this document require prior approval of the applicable Product Design Lead (PDL) or designee. Proposed changes shall be submitted in the EUROPA Propulsion Technical Data Management System (TDMS) via a Signature Control Request (SCORe) along with supportive material justifying the proposed change. Changes to this document will be made by complete revision.

All of the requirements in this document assume the use of the word "shall" unless otherwise stated.

Questions or comments concerning this document should be addressed to:

Europa Lander Propulsion Configuration Management Office Mail Stop: 597 Goddard Space Flight Center Greenbelt, Maryland 20771 iv Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

CHANGE HISTORY LOG

Revision Effective Date Description of Changes (Reference the SCORe Approval Date)

Revision - Released v Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

Table of Contents

1.0 Introduction

1.1 General Information

1.2 Scope

1.3 Applicable Documents

2.0 Management, Reporting, Reviews, and Documentation

2.1 Management of the Project

2.1.1 Project Manager

2.1.2 Lead Engineer

2.2 Reporting

2.2.1 Weekly Project Status Update

2.3 Reviews and Meetings

2.4 Documentation and Deliverables

2.5 Government Furnished data

3.0 Development

3.1 Meetings

3.1.1 Kickoff Meeting

3.1.2 Development Review

3.2 Documents

3.2.1 Project Plan and Schedule

3.3 Analysis & test

3.3.1 Planetary Protection

3.3.2 Passivation .................................................. Error! Bookmark not defined.

3.3.3 Computer Models

3.4 Documents

3.4.1 Qualification By Similarity (QBS) and Qual Plan

3.4.2 Parts, Materials and Processes List (PMPL)

3.4.3 Draft Interface Control Drawing (ICD)

4.0 Design and Manufacturing

4.1 Materials Requirements

4.1.1 Compatibility

4.1.2 Dissimilar Metals

4.1.3 Iron Nitrate

4.2 EEE Parts Design Requirements

4.2.1 Connectors/Wires Requirements

4.2.2 Coils

5.0 Quality Assurance

5.1 Quality Assurance Plan

5.2 Government Mandatory Inspection Points (MIPs)

5.3 System Safety Requirements

5.4 Workmanship Standards And Processes

5.4.1 Workmanship Requirements

5.4.2 Workmanship: Use of Alternate Workmanship Standards

Appendix A. Abbreviations and Acronyms vi Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

Appendix C DELIVERABLE PARTS LIST AND SCHEDULE (DILS) Appendix E. List of Applicable Documents vii Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

List of Tables Table 1 HMR Durations

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

1.0 INTRODUCTION

1.1 GENERAL INFORMATION

The Europa Lander mission is being formulated and implemented by a joint partnership between the Jet Propulsion Laboratory and the Applied Physics Laboratory, with NASA GSFC building the propulsion system for the Applied Physics Laboratory.

This SOW defines the work to be performed by the supplier to develop the Europa Lander Carrier Stage (CS) engines.

1.2 SCOPE

This Statement of Work (SOW) defines the supplier’s responsibilities under this project with respect to the tasks to be performed, the deliverables, the reporting requirements and all other elements required to successfully develop the Europa flight engines.

The engines to be developed under this contract shall meet all the requirements of Europa Lander Engine Specification LANDER-PROP-SPEC-0003. The development to be conducted under this contract have the objective of demonstrating preliminary compliance with requirements.

The supplier shall provide the facilities, personnel, services, tools, equipment, and materials as necessary to analyze, manufacture, test, and deliver the qualified hardware and test data and reports specified herein.

1.3 APPLICABLE DOCUMENTS

All reference documentation identified in this document shall apply in the situations where they are specifically referenced. Referenced documents are given in Appendix C.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

2.0 MANAGEMENT, REPORTING, REVIEWS, AND DOCUMENTATION

2.1 MANAGEMENT OF THE PROJECT

The supplier shall establish and apply a project control system for managing all resources, controlling schedules, managing all engineering, manufacturing and procurement activities, configuration management, and quality assurance

2.1.1 Project Manager

The supplier shall designate a Project Manager (PM) who has full responsibility and authority to manage all phases of the work during this project. The supplier’s Project Manager shall serve as the programmatic point of contact with the NASA GSFC Point Of Contact (GSFC POC) for all work during this project.

2.1.2 Lead Engineer

The supplier shall designate a Lead Engineer who shall report to the Project Manager and be the person primarily responsible for the technical aspects of this project.

The supplier’s Lead Engineer shall serve as the point of contact with the NASA GSFC Point Of Contact (GSFC POC) for all technical aspects of this project.

2.2 REPORTING

Reporting during this project shall consist of informal weekly telephone update, and reports as described in the following sections.

2.2.1 Weekly Project Status Update

The PM and lead engineer shall have a weekly telephone call of approximately one (1) hour duration with the GSFC POC. The purpose of this call is to update the GSFC POC on the status of the project activities. The topics shall include:

• Schedule

• Action Items

• Engineering Status, including analyses, process documents, and drawings

• Fabrication Status

• Test Status

• Documentation Status

• Review and meeting preparation

• ALL anomalies and non-conformances

• Any other topics determined to be needed by the PM to address project activities

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

2.3 REVIEWS AND MEETINGS

Only the meetings listed below are part of this contract.

1. Kickoff Meeting

2. Development Review

For these meetings the supplier shall provide WebEx and conference telephone services so people who are offsite can participate in these meetings.

2.4 DOCUMENTATION AND DELIVERABLES

The Delivery Items List and Schedule (DILS) is given in Appendix C. This appendix lists the deliverable items under this contract and the times when the deliveries are required to be made. Requirements for the various reports are given by reference to SOW paragraph numbers in the DILS. All documentation shall be submitted electronically.

The supplier shall ensure the generation and delivery of all documentation as called for in the contract and listed in the Deliverable Items List (DILS).

In addition to that documentation specifically called for in the contract, upon request by the GSFC POC, the supplier shall make available a copy of any document or data generated during this contract for review at either the supplier's facility or via electronic delivery to the GSFC POC. This includes, but is not limited to, technical reports and memorandums, drawings, schematics, studies, analyses, parts and materials data, test data, alerts, etc.

2.5 GOVERNMENT FURNISHED DATA

The government shall provide a preliminary engine specification with this SOW.

Additional drafts of the spec will be made available later, but shall not be binding on the scope of work of this contract without agreement by the vendor.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

3.0 DEVELOPMENT

The supplier shall do all of the design, analysis, manufacturing, testing, and documentation to develop the 20-lbf class engine.

3.1 MEETINGS

3.1.1 Kickoff Meeting

The supplier shall hold an informal Kickoff Meeting at the supplier’s facility within thirty

(30) days after contract award on a date mutually agreeable to GSFC and the vendor.

The supplier shall provide to the GSFC POC a Kickoff Meeting presentation package fourteen (14) calendar days prior to the meeting. Information to be included as part of the Kickoff Meeting agenda is described below and in other sections of this document.

The Kickoff Meeting shall cover:

• Project Management, including an organization chart

• Flight Heritage

• Development Engineering and test flow

• Facilities

• Subcontractors

• Project Plan

• SOW Compliance Matrix

• A preliminary list of technical requirements

• A preliminary qualification matrix

• A detailed schedule

3.1.2 Development Review

The supplier shall hold a development review at the supplier’s facility within one calendar year after contract award on a date mutually agreeable to GSFC, and the vendor. All developmental testing shall be complete prior to the development review.

The supplier shall provide to the GSFC POC a meeting presentation package fourteen

(14) calendar days prior to the meeting. Information to be included as part of the development review is described below and in other sections of this document.

The development review shall cover:

• The results of all developmental testing

• The schedule

• Any changes to the expected engine manufacturing

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• An updated list of technical requirements

• QBS and Qual Plan

• Draft ICD

• Updated Risks

The supplier is expected to provide sufficient technical details at this meeting such that GSFC can understand and evaluate the content provided.

3.2 DOCUMENTS

3.2.1 Project Plan and Schedule

The supplier shall develop a Project Plan and schedule that includes key milestones.

The supplier shall review this plan in detail at the Kick-off Meeting.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

3.3 ANALYSIS & TEST

3.3.1 Planetary Protection

The valve shall be subjected to a heat microbial reduction (HMR) process, with leakage and verified before and after the HMR. Heat microbial reduction is the process of elevating the temperature of the component or parts to a temperature of 116°C or greater for a prescribed time to reduce both surface and bulk bioburden. Table 1 shows the time/temperature requirements for HMR.

Table 1 HMR Durations

Temperature Time (hr) 116C 116.53 120C 102.99 125C 88.58 130C 76.53 135C 42.74 140C 24.21 145C 13.90 150C 8.08 155C 4.76 160C 2.84

3.3.2 Mechanical Models

The supplier shall deliver a simplified structural model for the engine in the form of a STEP file to be used in spacecraft design.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

3.4 DOCUMENTS

3.4.1 Qualification By Similarity (QBS) and Qual Plan

The Supplier shall provide a Qualification-By-Similarity (QBS) and Qual Plan to the GSFC POC 14 days prior to the development review. The purpose of this report is to document specification requirements that have been demonstrated during prior test activities as well as a plan for upcoming development. This report shall include detailed references to prior testing, including qualification test reports, where such data is used to verify compliance with specification requirements. The referenced qualification reports, test reports, test data and other relevant material shall be made available to the GSFC POC for review. Reports and test data which cannot be reviewed by the GSFC POC shall not be accepted as verifying a specification requirement. Any differences to referenced QBS items shall be documented in this report.

3.4.2 Parts, Materials and Processes List (PMPL)

The supplier shall create and maintain a Parts, Materials, and Processes list (PMPL).

The PMPL shall identify all materials and processes used in fabrication of the engine.

The PMPL will be provided to the GSFC POC at the Development Review.

3.4.3 Draft Interface Control Drawing (ICD)

The Supplier shall provide a draft interface control drawing (ICDs) for the engine.

These drawings shall provide draft versions of all electrical, thermal, and mechanical interfaces, including the center of mass and moments of inertia relative to an external reference. The mounting interfaces and center of mass shall be defined in the ICD.

These documents and/or drawings shall be delivered at the Development Review.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

4.0 DESIGN AND MANUFACTURING

Design and manufacturing requirements shall apply to all qualification hardware. Where practical, the same hardware should be used in development.

4.1 MATERIALS REQUIREMENTS

4.1.1 Compatibility

The engine, including all fluid paths, welds and braze joints, and valve parts shall show no degradation after a 10-year exposure to any of the following fluids:

• Nitrogen Tetroxide, (MON-3), per MIL-PRF-26539

• Monomethylhydrazine, per MIL-PRF-27404

The valve seat material shall be extruded perfluoroalkoxy (PFA) 450HP. No other valve seat material shall be used unless approved in writing by the GSFC POC (PFA has known radiation tolerance and compatibility).

The engines, including all fluid paths, exterior surfaces, welds and braze joints, shall show no degradation after a 6-month exposure to any of the following test fluids:

• Deionized and Distilled Water per JSC-SPEC-C-20C

• Isopropyl Alcohol per TT-I-735 (Grade A)

• Argon per MIL-PRF-27415A

• Gaseous Nitrogen per MIL-PRF-27401

• Ultra High Purity Gaseous Helium per MIL-PRF-27407

Hydrogen Peroxide Vapor (750 ppm)

After exposure to any of the above fluids, the engines shall be flushed and dried by a supplier-prepared and customer-approved procedure.

4.1.2 Dissimilar Metals

To avoid electrolytic corrosion, dissimilar metals should not be used in direct contact unless protection against corrosion has been provided in accordance with MIL-STD-

889. Variances from this policy must be submitted to the GSFC POC for approval.

4.1.3 Iron Nitrate

The use of steel on the wetted path shall be minimized.

4.1.4 Chamber Materials

The chamber shall be made of Iridium/Rhenium unless approved by the COR.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

4.2 EEE PARTS DESIGN REQUIREMENTS

Any deviations to section 4.2 shall be provided to the NASA GSFC COR.

4.2.1 Connectors/Wires Requirements

4.2.1.1 Leadwire Types

All leadwires shall be twisted shielded pairs or triples with no insulation jacket (i.e., M27500C22SC2S00, M27500C26SC3S00, or similar wire approved by the POC). The connections for each coil shall form a separate 22 AWG shielded pair.

4.2.1.2 Minimum Wire Size

No wire smaller than AWG #26 shall be used with the exception of solenoid wire. The size of solenoid wire shall be provided to the POC at the DCR. Any lead wire larger than AWG #22 shall require approval by the POC.

4.2.1.3 Wire Derating

The current carrying capacity of the wires shall be derated for continuous operation at the required current levels in a vacuum, as defined in Section W1 of EEE-INST-002.

4.2.1.4 Wire Composition

Wire conductors shall be copper or a copper alloy. The wires may be tinned or plated with suitable materials except nickel or other magnetic materials. Suitable handling and storage precautions shall be used for the wire type as called out in EEE-INST-002.

4.2.2 Coils

4.2.2.1 Non-Custom Coil Designs

If non-custom coils are used, MIL-PRF-15305 coils shall not be used. If using MIL-PRF- 39010 coils, Failure Rate Level (FRL) R shall be the minimum acceptable design. If using MIL-PRF-27 coils, screening shall be performed per MIL-PRF-27, Group A and B for Product Level T.

4.2.2.2 Coil Testing

Lot specific variables and attributes data for 100% screening and sample qualifications tests shall be submitted to show that tests were performed with acceptable results in the same lot/date code, same manufacturer on the same manufacturing line. Data shall be for the actual lot of parts that are intended for flight use. Generic or similarity screening and qualification data is not acceptable.

Use or disclosure of data contained on this page is subject to the restriction(s) on the first page of this document.

4.2.2.3 Magnet Wire

All magnet wire shall be NEMA/ANSI MW-1000 per a Certification of Conformance by manufacturer, including MW-1000 part number and lot/date code, or equivalent.

All magnet wire shall be non-lubricant MW-1000 letter N or lubricated with Paraffin (MW-1000 letter P). No unspecified lubrication shall be used (MW-1000 letter U) within the valve.

All magnet wire shall have a minimum of Heavy insulation (2 coats). Exceptions shall be submitted in writing to the POC for review.

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5.0 QUALITY ASSURANCE

5.1 QUALITY ASSURANCE PLAN

The supplier shall implement a Quality Management System that meets with the intent of the requirements of American Standards Institute (ANSI)/ISO, American Society for Quality (ASQ) Q9001 (2008 version) or equivalent, as documented in a Quality Assurance Plan.

5.2 GOVERNMENT MANDATORY INSPECTION POINTS (MIPS)

There are no formal MIPs. Key test shall be reported to the NASA GSFC in sufficient time to allow optional attendance.

5.3 SYSTEM SAFETY REQUIREMENTS

The supplier shall supply detailed descriptions of the design, test, operation and inspection requirements for all flight hardware and materials, ground support equipment, and their interfaces necessary for a valid identification, assessment, control and mitigation of documented hazards. This includes technical information concerning hazardous and safety critical equipment, systems, operations, handling and materials.

For all identified hazards, the supplier shall also document hazard controls, verifications and tracking methods.

5.4 WORKMANSHIP STANDARDS AND PROCESSES

5.4.1 Workmanship Requirements

The following workmanship standards shall apply to the engine.

• NASA-STD-8739.4, Crimping, Interconnecting Cables, Harnesses, and Wiring, dated February 9, 1998, with Change 6, dated March 29, 2011

• ANSI/NCSL 2540.3, Requirements for the Calibration of Measuring and Test Equipment

• ISO9001-2008, AS9100, AS9120, AS9003, AC7004, ISO17025, ISO16949 or

ISO13485, Quality Management Systems – Aerospace – Requirements

5.4.2 Workmanship: Use of Alternate Workmanship Standards

GSFC recognizes that the supplier may have an established workmanship project equivalent to the specific standards cited herein. In these instances, the supplier may use existing standards upon review and approval by the GSFC POC. It must be established that the supplier’s workmanship project fully encompasses the specific requirements of this chapter.

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APPENDIX A. ABBREVIATIONS AND ACRONYMS

Abbreviation/ Acronym Definition

ABML As-Built Materials List ABPL As-Built Parts List ANSI American National Standards Institute ACA After Contract Award CCB Configuration Control Board CCP Contamination Control Plan CCR Configuration Change Request CM Configuration Management CO Contracting Officer CVCM Collected Volatile Condensable Mass DCR Design Conformance Review EEE Electrical, Electronic, and Electromechanical EPW Electrical Pulse Width ESD Electrostatic-Discharge FMECA Failure Modes Effects and Criticality Analysis FRB Failure Review Board GIDEP Government Industry Data Exchange Project GSE Ground Support Equipment GSFC Goddard Space Flight Center MIS Management Information System MIP Mandatory Inspection Point MMH Monomethylhydrazine MRB Material Review Board MUA Materials Usage Agreement NASA National Aeronautics and Space Administration PDL Product Design Lead POC Point Of Contact PSR Pre-Ship Review QA Quality Assurance SCC Stress GSFC Corrosion Cracking SCORe Signature Controlled Request S/C Spacecraft SOW Statement of Work TBD To Be Determined TBR To Be Resolved TIM Technical Interchange Meeting

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APPENDIX C DELIVERABLE PARTS LIST AND SCHEDULE (DILS)

The hardware and document deliveries for this contract are listed below.

All document deliveries shall be in electronic format.

Two copies of each document shall be delivered: one (1) copy to the GSFC Contracting Officer’s Representative (POC) and one (1) copy to the GSFC Contracting Officer (CO).

Phase 1

Meetings

Item SOW Ref

Title Delivery Date

1 3.1.1 Kickoff Meeting 30 days After Contract Award (ACA) 2 3.1.2 Development Review (DR) 1 Year ACA

Deliverables

Item SOW Ref

Title Delivery Milestone(s)

1 3.2.1 Project Plan and Schedule Kickoff 2 3.4.1 QBS and Qualification Plan DR

3 3.4.2 PMPL DR

4 3.4.3 Draft ICD DR 5 3.3.2 Mechanical Model DR

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APPENDIX E. LIST OF APPLICABLE DOCUMENTS

All referenced documentation identified in the SOW shall apply in the situations where they are specifically referenced.

Document Number Title Revision/Date

EUROPA-PROP-

SPEC-0010

Europa Project Engine Specification Rev C 9/8/2010

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

04/01/08

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

11/28/1984

GSFC-STD-7000 General Environmental Verification Standard (GEVS) for GSFC Flight Projects and Projects

04/2005 TBR

SAE AS9100 Quality Systems Aerospace - Model for Quality Assurance in Design, Development, Production, Installation, and Servicing

11/1999

NASA-STD-8739.4 Crimping, Interconnecting Cables, Harnesses, and Wiring

02/09/98

ANSI/ESD S20.20-

Protection of Electrical and Electronic Parts, Assemblies and Equipment (Excluding Electrically Initiated Explosive Devices)

05/16/1999

ASTM E-595 Standard test method for total mass loss and collected volatile condensable materials from outgassing in a vacuum environment

1993 (R03)E1

MSFC-STD-3029 Multiproject/project common-use document guidelines for the selection of metallic materials for stress GSFC corrosion cracking resistance in sodium chloride environments

05/22/2000

ASTM E1742 Standard Practice for Radiographic Examination

NASA-RP-1124-Rev-4 Outgassing Data for Selecting Spacecraft Materials

06/1997

J-STD-001ES Joint Industry Standard, Space Applications Electronic Hardware Addendum to J-STD-001E

12/2001

JPL-D-80302, Rev. A Environmental Requirements Document

10/16/2017