NASA-STD-(I)-5009, NONDESTRUCTIVE EVALUATION REQUIREMENTS FOR FRACTURE CRITICAL METALLIC COMPONENTS

NASA-STD-(I)-5009, NONDESTRUCTIVE EVALUATION REQUIREMENTS FOR FRACTURE CRITICAL METALLIC COMPONENTS. The purpose of this standard is to establish the nondestructive evaluation (NDE) requirements for fracture control of all aerospace flight systems including manned and unmanned spaceflight systems, manned and unmanned aeronautical systems, payloads, flight experiments and associated ground based hardware. This standard defines the primary requirements for NDE in support of NASA-STD-5007, General Fracture Control Requirements for Manned Spaceflight Systems. NDE applied in-process for purposes of process control is not addressed in this document.

NASA-STD-(I)-5019, FRACTURE CONTROL REQUIREMENTS FOR SPACEFLIGHT HARDWARE

NASA-STD-(I)-5019, FRACTURE CONTROL REQUIREMENTS FOR SPACEFLIGHT HARDWARE. This Interim Technical Standard is published by the National Aeronautics and Space Administration (NASA) to provide uniform engineering and technical requirements for processes, procedures, practices, and methods that have been endorsed as standard for NASA programs and projects, including requirements for selection, application, and design criteria of an item. This standard is approved for use by NASA Headquarters and NASA Centers, including Component Facilities. This document establishes the fracture control requirements (replacing NASA-STD-5007) for all human-rated spaceflight systems, payloads, propulsion systems, orbital support equipment, and planetary habitats. It was developed by a NASA-wide Fracture Control Working Group to harmonize and provide a common framework for fracture control practices on NASA programs.

NASA-STD-(I)-6008, NASA FASTENER MANAGEMENT AND CONTROL PRACTICES

NASA-STD-(I)-6008, NASA FASTENER MANAGEMENT AND CONTROL PRACTICES. This Interim Technical Standard is published by the National Aeronautics and Space Administration (NASA) to provide uniform engineering and technical requirements for processes, procedures, practices, and methods that have been endorsed as standard for NASA programs and projects, including requirements for selection, application, and design criteria of an item. This standard is approved for use by NASA Headquarters and NASA Centers, including Component Facilities. This standard defines fastener integrity requirements for all fasteners used in flight hardware and for critical nuts and bolts used on ground support equipment (GSE), including all flight hardware/GSE interfaces.

NASA-STD-(I)-6016, STANDARD MATERIALS AND PROCESS REQUIREMENTS FOR SPACECRAFT

NASA-STD-(I)-6016, STANDARD MATERIALS AND PROCESS REQUIREMENTS FOR SPACECRAFT. This document is directed toward Materials and Processes (M&P) used in the design, fabrication, and testing of flight components for all NASA manned, unmanned, robotic, launch vehicle, lander, in-space and surface systems, and spacecraft program/project hardware elements. All flight hardware is covered by the M&P requirements of this document, including vendordesigned, off- the-shelf, and vendor furnished items. Materials and processes used in interfacing ground support equipment (GSE); test equipment; hardware processing equipment; hardware packaging; and hardware shipment shall be controlled to prevent damage to or contamination of flight hardware.

NASA-STD-(I)-7009, STANDARD FOR MODELS AND SIMULATIONS

NASA-STD-(I)-7009, STANDARD FOR MODELS AND SIMULATIONS. The primary goal of this standard is to ensure that the credibility of the results from models and simulations (M&S) is properly conveyed to those making critical decisions. This will support risk-informed decisions. (By “critical decisions” we mean decisions that may affect human safety or project defined mission success criteria.) The secondary goal is to assure that the credibility of the results from M&S meets the project requirements. This will reduce the risks associated with critical decisions. This standard covers the development and operation (or execution) of the M&S, as well as the analysis and presentation of the results from the simulations.

NASA-STD-0005 (DRAFT 72), NASA CONFIGURATION MANAGEMENT (CM) STANDARD

NASA-STD-0005 (DRAFT 7.2), NASA CONFIGURATION MANAGEMENT (CM) STANDARD. This Standard provides CM requirements and guidance for NASA Centers, Programs/Projects, and NASA Suppliers. This Standard contains CM requirements for the NASA systems defined in NPR 7120.5, “NASA Program/Project Management Processes and Requirements.”

NASA-STD-2201-93 (NASA TM-10970), SOFTWARE ASSURANCE STANDARD

NASA-STD-2201-93 (NASA TM-10970), SOFTWARE ASSURANCE STANDARD. This Standard specifies the software assurance program for the provider of software. It also delineates the assurance activities for the provider and the assurance data that are to be furnished by the provider to the acquirer. In any software development effort, the provider is the entity or individual that actually designs, develops, and implements the software product, while the acquirer is the entity or individual who specifies the requirements and accepts the resulting products.

NASA-STD-4003, ELECTRICAL BONDING FOR NASA LAUNCH VEHICLES, SPACECRAFT, PAYLOADS, AND FLIGHT EQUIPMENT

FOREWORD This standard is approved for use by NASA Headquarters and all NASA Centers and provides a common framework for consistent electrical bonding practices across NASA programs. The intent of this NASA standard is to provide stand-alone requirements and to provide enough data to help modify requirements or to allow waivers if needed. Requests for information, corrections, or additions to this standard should be directed to the Electromagnetic Environmental Effects Team, ED44/4708, MSFC, AL 35812. Requests for general information concerning NASA Technical Standards should be sent to the NASA Technical Program Standards Office, ED41 MSFC, AL 35812, (telephone 256-544-2448). This and other NASA standards may be viewed and downloaded, free-of-charge, from our NASA Standards Homepage: http://standards.nasa.gov. Original Signed By Theron M. Bradley, Jr. NASA Chief Engineer

NASA-STD-4005, LOW EARTH ORBIT SPACECRAFT CHARGING DESIGN STANDARD

NASA-STD-4005, LOW EARTH ORBIT SPACECRAFT CHARGING DESIGN STANDARD.This standard provides requirements relative to various plasma interactions that can result when a high-voltage system is operated in the Earth’s ionosphere and standard practices to eliminate or mitigate such reactions. the purpose of this standard is to provide a design standard for high-voltage space power systems (> 55 volts (V)) that operate in the plasma environment associated with LEO (altitude from 200 and 1000 km and latitude between -50 and +50 degrees). Such power systems, particularly solar arrays, are the proximate cause of spacecraft charging in LEO; and these systems can interact with this environment in a number of ways that are potentially destructive to themselves as well as to the platform or vehicle that has deployed them.

NASA-STD-5001, STRUCTURAL DESIGN AND TEST FACTORS OF SAFETY FOR SPACEFLIGHT HARDWARE

NASA-STD-5001, STRUCTURAL DESIGN AND TEST FACTORS OF SAFETY FOR SPACEFLIGHT HARDWARE. This standard establishes structural strength design and test factors, as well as service life factors to be used for spaceflight hardware development and verification. It is intended to reduce space project costs and schedules by enhancing the commonalty of use of hardware designs between NASA flight projects, Centers, and their contractors. While it is true that structural designs are sometimes governed by criteria other than strength, the criteria in this document are to be considered as minimum acceptable values unless adequate engineering risk assessment is provided which justifies the use of lower values.

NASA-STD-5002, LOAD ANALYSES OF SPACECRAFT AND PAYLOADS

NASA-STD-5002, LOAD ANALYSES OF SPACECRAFT AND PAYLOADS. This standard defines the methodologies, practices, and requirements for the conduct of load analyses for payloads and spacecraft. This standard establishes general NASA policies for the definition of loads to be used in the design and development of payloads and spacecraft. Guidelines are prescribed to establish consistent practices and facilitate integration at the project and program levels. Payloads and spacecraft shall be designed to maintain structural integrity and the required degree of functionality to ensure successful operation during all phases of the expected life cycle. Flight structures and systems shall consider static and dynamic load environments to be encountered during assembly, testing, transportation, launch, ascent, space operations, extraterrestrial operations, descent, and landing.

NASA-STD-5003, FRACTURE CONTROL REQUIREMENTS FOR PAYLOADS USING THE SPACE SHUTTLE

NASA-STD-5003, FRACTURE CONTROL REQUIREMENTS FOR PAYLOADS USING THE SPACE SHUTTLE (PREVIOUS VERSION PUBLISHED AS NHB 8071.1). The purpose of this document is to establish the fracture control requirements for all payload hardware to be launched or retrieved using the Space Shuttle. Meeting these requirements implements the minimum fracture control requirements of National Space Transportation System (NSTS) 1700.7, Safety Policy and Requirements for Payloads Using the Space Transportation System. All payload fracture control shall be in accordance with the requirements stated herein.

NASA-STD-5005, GROUND SUPPORT EQUIPMENT DESIGN CRITERIA.

NASA-STD-5005, GROUND SUPPORT EQUIPMENT DESIGN CRITERIA. This standard establishes the general characteristics, performance, liability, maintainability, supportability, and quality requirements for ground support systems and equipment intended for use at NASA launch, landing, or retrieval locations. This standard specifies the criteria to provide simple, robust, safe, reliable, maintainable, supportable, and cost-effective ground support equipment (GSE) necessary to support space vehicle and payload launch operations.

NASA-STD-5008A, PROTECTIVE COATING OF CARBON STEEL, STAINLESS STEEL, AND ALUMINUM ON LAUNCH STRUCTURES, FACILITIES, AND GROUND SUPPORT EQUIPMENT

NASA-STD-5008A, PROTECTIVE COATING OF CARBON STEEL, STAINLESS STEEL, AND ALUMINUM ON LAUNCH STRUCTURES, FACILITIES, AND GROUND SUPPORT EQUIPMENT. This standard is approved for use by NASA Headquarters and all NASA Centers and is intended to provide a common framework for consistent practices across NASA programs. This standard was developed to establish uniform engineering practices and methods and to ensure the inclusion of essential criteria in the coating of ground support equipment (GSE) and facilities used by or for NASA. This standard is applicable to GSE and facilities that support space vehicle or payload programs or projects and to critical facilities at all NASA locations worldwide. The John F. Kennedy Space Center Spaceport Engineering and Technology Directorate developed this standard. This standard establishes practices for the protective coating of GSE and related facilities used by or for NASA programs and projects. This standard is for the design of nonflight hardware used to support the operations of receiving, transportation, handling, assembly, inspection, test, checkout, service, and launch of space vehicles and payloads at NASA launch, landing, or retrieval sites. These criteria and practices may be used for items used at the manufacturing, development, and test sites upstream of the launch, landing, or retrieval sites. The information provided herein shall be used for the preparation of written, individual coating specifications for specific projects for the prevention of corrosion through the use of protective coatings on facilities, space vehicle launch structures, and ground support equipment in all environments. Due to the changing environmental considerations, new advances in corrosion control technology, and the wide array of possible applications, this document should not be used as a stand-alone specification that meets every contingency.

NASA-STD-5012, STRENGTH AND LIFE ASSESSMENT REQUIREMENTS FOR LIQUID FUELED SPACE PROPULSION SYSTEM ENGINES

NASA-STD-5012, STRENGTH AND LIFE ASSESSMENT REQUIREMENTS FOR LIQUID FUELED SPACE PROPULSION SYSTEM ENGINES. This standard provides strength and life assessment requirements for National Aeronautics and Space Administration (NASA) liquid fueled space propulsion system engines. "Life," as used in this standard, refers to fatigue and creep. The requirements address analyses and tests to qualify an engine structurally. The total system requirements for engine hot-fire tests are not addressed in these requirements; however, a minimum number of such tests must be conducted in conjunction with structural analyses and tests to qualify the engine structurally. These requirements define the minimum structural requirements acceptable to NASA. These requirements specify analyses and test factors, margins, and other parameters where appropriate. In some cases, these requirements are expressed by reference to other standards

NASA-STD-5017, DESIGN AND DEVELOPMENT REQUIREMENTS FOR MECHANISMS.

NASA-STD-5017, DESIGN AND DEVELOPMENT REQUIREMENTS FOR MECHANISMS. The purpose of this standard is to establish common design and development requirements across National Aeronautics and Space Administration (NASA) Centers for the design of aerospace mechanisms whose correct operation is required for safety or program success. Collecting the requirements in a NASA standard allows each NASA program to rely upon an established set of practices that have proved heritage and that have been developed from lessons learned across a spectrum of design applications. This standard is designed to be applied to flight mechanisms that are designed, built, or acquired by or for NASA, though it may also serve as a useful guidance document for other systems such as ground support equipment (GSE). This document addresses technical functional requirements only and specifically does not address human factors requirements.

NASA-STD-6001, FLAMMABILITY, ODOR, OFFGASSING,AND COMPATIBILITY REQUIREMENTS AND TEST PROCEDURES FOR MATERIALS IN ENVIRONMENTS THAT SUPPORT COMBUSTION

NASA-STD-6001, NASA TECHNICAL STANDARD, FLAMMABILITY, ODOR, OFFGASSING,AND COMPATIBILITY REQUIREMENTS AND TEST PROCEDURES FOR MATERIALS IN ENVIRONMENTS THAT SUPPORT COMBUSTION (PREVIOUSLY PUBLISHED AS NHB 8060.1C). This standard is approved for use by NASA Headquarters and all Field Centers and is intended to provide a common framework for consistent practices across NASA programs. This document establishes requirements for evaluation, testing, and selection of materials that are intended for use in space vehicles, associated ground support equipment, and facilities used during assembly, test, and flight operations. Included are requirements, criteria, and test methods for evaluating the flammability, odor, offgassing, and compatibility of materials. Provisions of this standard will be included, as applicable, in all future contracts and programs involving space vehicles, payloads, and associated support equipment. This document was previously published as NHB 8060.1.

NASA-STD-6002C, APPLYING DATA MATRIX IDENTIFICATION SYMBOLS ON AEROSPACE PARTS

NASA-STD-6002C, APPLYING DATA MATRIX IDENTIFICATION SYMBOLS ON AEROSPACE PARTS. This standard is published by the National Aeronautics and Space Administration (NASA) to provide uniform engineering and technical requirements for processes, procedures, practices, and methods that have been endorsed as standard for NASA programs and projects, including requirements for selection, application, and design criteria of an item. This standard is approved for use by NASA Headquarters and NASA Centers, including Component Facilities. This standard establishes uniform requirements for applying Data Matrix identification symbols to parts used on NASA programs/projects using direct part marking (DPM) methods and techniques. Requests for information, corrections, or additions to this standard should be submitted via “Feedback” in the NASA Technical Standards System at http://standards.nasa.gov.

NASA-STD-7001, Payload Vibroacoustic Test Criteria

The primary objective of this standard is to establish a uniform usage of test factors in the vibro-acoustic verification process for spaceflight payload hardware.

NASA-STD-7002, PAYLOAD TEST REQUIREMENTS

NASA TECHNICAL STANDARD. This standard provides a NASA-wide common basis from which test programs shall be developed for NASA payloads. The document defines a succinct standard set of flight hardware test requirements which provide for the necessary verification of design adequacy and flight worthiness of NASA spacecraft. Compliance provides consistency across the Agency and its contractors, thereby facilitating the sharing of hardware between Centers and programs. Compliance also provides a basis for establishing a baseline pedigree that allows the conduct of a "qualification by similarity" evaluation process for "heritage" hardware without the complicating need to consider the variability of test requirements.

NASA-STD-7003, PYROSHOCK TEST CRITERIA

NASA-STD-7003, PYROSHOCK TEST CRITERIA. The objective of this NASA Technical Standard is to provide a consistent methodology for developing pyroshock test criteria for NASA spacecraft, payload, and launch vehicle hardware during the development, qualification, flight acceptance, and/or protoflight test phases of the verification process. Various aspects of pyroshock testing are discussed herein, including test environments, methods and facilities, test margins and number of exposures, control tolerances (when applicable), data acquisition and analysis, test tailoring, dynamic analysis, and prediction techniques for pyroshock environments.

NASA-STD-7004, FORCE LIMITED VIBRATION TESTING

NASA-STD-7004, FORCE LIMITED VIBRATION TESTING. This handbook establishes a methodology for conducting force limited vibration tests for all NASA flight projects. The purpose is to provide an approach which may be consistently followed by those desiring to use force limiting, without having to conduct an extensive literature search or research and development effort before conducting the test. A monograph on Force Limited Vibration Testing is available for reference and is recommended for those needing more detailed technical information (NASA-RP-1403).

NASA-STD-8709.2, NASA SAFETY AND MISSION ASSURANCE ROLES AND RESPONSIBILITIES FOR EXPENDABLE LAUNCH VEHICLE SERVICES

NASA-STD-8709.2, NASA SAFETY AND MISSION ASSURANCE ROLES AND RESPONSIBILITIES FOR EXPENDABLE LAUNCH VEHICLE SERVICES. This document defines the NASA Safety and Mission Assurance (SMA) roles and responsibilities as they apply to the various commercial launch service procurement methodologies. The document addresses the NASA SMA functions required for each mission phase from procurement through design, production, launch vehicle integration, spacecraft integration, system test, prelaunch operations, launch operations, post launch activities and mishap investigations. The document is not meant to assign SMA Roles and Responsibilities to a particular organizational unit.

NASA-STD-8719-9, STANDARD FOR LIFTING DEVICES AND EQUIPMENT

NASA-STD-8719-9, STANDARD FOR LIFTING DEVICES AND EQUIPMENT. This standard applies to overhead and gantry cranes (including top running monorail, underhung, and jib cranes) mobile cranes, derricks, hoists, winches, special hoist supported personnel lifting devices, hydra-sets, load measuring devices, hooks, slings and rigging, mobile aerial platforms, powered industrial trucks, and jacks. This document does not include coverage for front-end loaders and elevators. 1.2 Purpose. This standard establishes NASA's minimum requirements for the design, testing, inspection, maintenance, personnel certification, and operation of lifting devices and equipment (LDE) described in paragraph 1.1. 1.3 Applicability. Compliance with this standard is mandatory for all NASA-owned and NASA contractor-supplied equipment used in support of NASA operations at NASA installations and NASA operations in host countries. The individual installation Lifting Devices and Equipment Manager (LDEM) and safety organizations are responsible for implementation and enforcement. This document establishes minimum requirements; NASA installations should assess their individual programs and develop additional requirements as needed. The need for compliance with this standard at contractor installations performing NASA work should be evaluated and made a contractual requirement where deemed necessary by the contracting officer and the responsible NASA installation/program safety office. Rented or leased LDE is exempt from this standard only by the decision of the contracting officer, the responsible NASA installation/program safety office, and the LDEM. If determined that rented or leased LDE will be used for a critical lift, this standard applies. 1.3.1 The testing, inspection, maintenance, operational, and operator and rigger certification/recertification/licensing requirements apply to new and existing lifting devices and equipment. 1.3.2 The design/hardware requirements contained in this document are applicable to new lifting devices/equipment purchased after 6 months from the issue date of this document. Existing equipment and that purchased during the first 6 months from issue of this document shall be reviewed for compliance with all design/hardware aspects of this standard within 12 months of its issue and the need to update such equipment shall be evaluated. 1.3.3 Deviations/waivers from the requirements of this document (including design/hardware requirements for both new and existing equipment) shall be approved as outlined in paragraph 1.7. The deviation/waiver documentation shall include any alternate or special criteria or procedures that will be imposed to ensure safe design and operations for those devices that do not meet the applicable requirements. 1.3.4 Portions of this standard refer to various national consensus codes/standards for equipment design/hardware requirements (e.g., ASME, CMAA, etc.). Lifting devices and equipment purchased after the initial review required in paragraph 1.3.2 shall comply with the specified codes/standards in effect at the time of manufacture. Each installation shall periodically review subsequent codes/standards and evaluate the need to update existing equipment. Based on an evaluation of NASA's overall safe lifting program and any significant changes in the consensus codes/standards, the NASA Safety and Risk Management Division.

NASA-STD-8719.10, STANDARD FOR UNDERWATER FACILITY AND NON-OPEN WATER OPERATIONS

NASA-STD-8719.10, STANDARD FOR UNDERWATER FACILITY AND NON-OPEN WATER OPERATIONS. This standard covers all NASA neutral buoyancy facilities, equipment, personnel, and operations involving non-open water underwater activities that provide simulation of weightless environment.

NASA-STD-8719.11 (W/ CHANGE 3), SAFETY STANDARD FOR FIRE PROTECTION

NASA-STD-8719.11 (W/ CHANGE 3), SAFETY STANDARD FOR FIRE PROTECTION. This Safety Standard establishes a uniform, comprehensive NASA Fire Protection Program. It contains minimum fire safety requirements and guidelines applicable to NASA Headquarters and all NASA Centers. This standard expands on the policy and guidelines for fire protection listed in Chapter 9 of NPG 8715.3, “NASA Safety Manual.” It is a compilation of pertinent requirements from the Occupational Safety and Health Administration (OSHA), National Fire Protection Association (NFPA), and unique NASA requirements. The intent is to combine the knowledge of all NASA Centers, standardize definitions, and develop uniform requirements. This document is not intended to be a substitute for Federal or applicable State and local government requirements.

NASA-STD-8719.13B, NASA TECHNICAL STANDARD, SOFTWARE SAFETY STANDARD

NASA-STD-8719.13B (W/ CHANGE 1), NASA TECHNICAL STANDARD, SOFTWARE SAFETY STANDARD. (REPLACES NASA-STD-8719.13A DATED SEPTEMBER 1997 This Standard specifies the software safety activities, data, and documentation necessary for the acquisition or development of software in a safety-critical system. Safety-critical systems that include software must be evaluated for software’s contribution to the safety of the system during the concept phase, and prior to the start, or in the early phases, of the acquisition or planning for the given software. Unless the evaluation proves that the software is not involved in the system safety, this Standard is to be followed. See section 1.2 for guidance, and section 4.1 for requirements (and definition), on the determination of safety-critical software.

NASA-STD-8719.14, PROCESS FOR LIMITING ORBITAL DEBRIS

NASA-STD-8719.14, PROCESS FOR LIMITING ORBITAL DEBRIS. This document serves as a companion to NASA Procedural Requirements (NPR) 8715.6 and provides specific requirements and methods to comply with the NASA requirements for limiting orbital debris generation. NASA-Standard (NASA-STD) 8719.14 updates NASA Safety Standard (NSS) 1740.14, which went into effect in August 1995. This NASA-STD helps ensure that spacecraft and launch vehicles meet acceptable standards for limiting orbital debris generation.

NASA-STD-8719.17, NASA Requirements for Ground-Based Pressure Vessels and Pressurized Systems (PV/S)

NASA-STD-8719.17, NASA Requirements for Ground-Based Pressure Vessels and Pressurized Systems (PV/S. The purpose of this document is to ensure the structural integrity of PV/S through implementation of the minimum requirements for ground-based PV/S in accordance with this document, NASA Policy Directive (NPD) 8710.5, NASA Safety Policy for Pressure Vessels and Pressurized Systems, NASA Procedural Requirements (NPR) 8715.3, NASA General Safety Program Requirements, applicable Federal Regulations, and national consensus codes and standards (NCS).

NASA-STD-8719.8, EXPENDABLE LAUNCH VEHICLE PAYLOAD SAFETY REVIEW PROCESS STANDARD

NASA-STD-8719.8, EXPENDABLE LAUNCH VEHICLE PAYLOAD SAFETY REVIEW PROCESS STANDARD. This document assists NASA payload developers and managers by describing what needs to be done to get a payload through the safety review process and certify that it is safe to process and launch in compliance with applicable safety requirements. The safety review process presented in this document is tailorable and applicable to orbital and suborbital payloads launched by various classes of expendable launch vehicles including sounding rockets and balloons. NASA safety policy is to maintain the assurance of safe design, operation, and processing of a payload and its support equipment. Requirements for assuring payload mission success are the responsibility of the payload organization and are beyond the scope of this document.

NASA-STD-8719.9 (W/ CHANGE 1), STANDARD FOR LIFTING DEVICES AND EQUIPMENT

NASA-STD-8719.9 (W/ CHANGE 1), STANDARD FOR LIFTING DEVICES AND EQUIPMENT. This standard applies to overhead and gantry cranes (including top running monorail, underhung, and jib cranes) mobile cranes, derricks, hoists, winches, special hoist supported personnel lifting devices, hydra-sets, load measuring devices, hooks, slings and rigging, mobile aerial platforms, powered industrial trucks, and jacks. This document does not include coverage for front-end loaders and elevators.

NASA-STD-8729.1, PLANNING, DEVELOPING AND MANAGING AN EFFECTIVE RELIABILITY AND MAINTAINABILITY (R&M) PROGRAM

NASA-STD-8729.1, PLANNING, DEVELOPING AND MANAGING AN EFFECTIVE RELIABILITY AND MAINTAINABILITY (R&M) PROGRAM. This standard provides guidance to customers or purchasers and suppliers or contractors on R&M requirements development, design implementation, and evaluation.

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

NASA-STD-8739.1, Workmanship Standard for Staking and Conformal Coating of Printed Wiring Boards and Electronic Assemblies. Workmanship Standard for Staking and Conformal Coating of Printed Wiring Boards and Electronic Assemblies. This standard prescribes NASA's requirements, procedures, and documenting requirements for staking and conformal coating of printed wiring boards and electronic assemblies.

NASA-STD-8739.2, WORKMANSHIP STANDARD FOR SURFACE MOUNT TECHNOLOGY

NASA-STD-8739.2, WORKMANSHIP STANDARD FOR SURFACE MOUNT TECHNOLOGY. This document has been issued to make available to project managers a technical standard where surface mount attachment techniques are to be used. The document: Prescribes NASA's requirements, procedures, and documenting requirements for hand and machine soldering of surface mount electrical connections. These may be tailored to the program applications to obtain the most cost effective, best quality product. Describes basic considerations necessary to ensure reliable soldered surface mount connections. Establishes the responsibility for documentation of those fabrication and inspection procedures to be used for NASA work including supplier innovations, special processes, and changes in technology. For the purpose of this document the term supplier is defined as in-house NASA, NASA contractors, and subtier contractors. Procuring NASA Enterprise Programs or Centers shall review this document for applicability to NASA contracts as well as for applicability to its internal activities. Questions concerning the application of this publication to specific procurements or requests should be referred to the NASA Enterprise Program or Center. Comments and suggestions for improving this publication may be submitted using the form "NASA Standard Improvement Proposal." A copy of this form is included at the end of the document. Other processes such as conformal coating or cabling and harnessing not covered by this document may be required to fabricate hardware involving surface mounted devices. The design, materials, and processes not covered shall be defined in engineering documentation. This Standard cancels NASA Assurance Standard 5300.4(3M), Workmanship Standard for Surface Mount Technology.

NASA-STD-8739.3-2, Soldered Electrical Connections

NASA-STD-8739.3-2, Soldered Electrical Connections This standard provides the baseline for NASA project offices to use when preparing or evaluating process procedures for the manufacture of space flight hardware or mission critical ground support equipment.

NASA-STD-8739.4 (w/ CHANGE 3), CRIMPING, INTERCONNECTING CABLES, HARNESSES, AND WIRING (FEB 1998) [PREVIOUS VERSION PUBLISHED AS NAS 5300.4(3G-1)]

NASA-STD-8739.4 (w/ CHANGE 3), CRIMPING, INTERCONNECTING CABLES, HARNESSES, AND WIRING (FEB 1998) [PREVIOUS VERSION PUBLISHED AS NAS 5300.4(3G-1)] ., This publication sets forth requirements for interconnecting cable and harness assemblies that connect electrical/electronic and electromechanical components.

NASA-STD-8739.4 (w/ CHANGE 3), CRIMPING, INTERCONNECTING CABLES, HARNESSES, AND WIRING (FEB 1998) [PREVIOUS VERSION PUBLISHED AS NAS 5300.4(3G-1)]

NASA-STD-8739.4 (w/ CHANGE 3), CRIMPING, INTERCONNECTING CABLES, HARNESSES, AND WIRING (FEB 1998) [PREVIOUS VERSION PUBLISHED AS NAS 5300.4(3G-1)] ., This publication sets forth requirements for interconnecting cable and harness assemblies that connect electrical/electronic and electromechanical components.

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

NASA-STD-8739.5 Fiber Optic Terminations, Cable Assemblies, and Installation. This standard provides a baseline for NASA project offices to use when preparing or evaluating process procedures for the manufacture of space flight hardware or mission critical ground support equipment.

NASA-STD-8739.7, ELECTROSTATIC DISCHARGE CONTROL (EXCLUDING ELECTRICALLY INITIATED EXPLOSIVE DEVICES)

NASA-STD-8739.7, ELECTROSTATIC DISCHARGE CONTROL (EXCLUDING ELECTRICALLY INITIATEd EXPLOSIVE DEVICES). This document has been CANCELLED. This publication sets forth ESD control requirements for items that are ESD Sensitive (ESDS)(excluding electrically initiated explosive devices).

NASA-STD-8739.8 (w/ CHANGE 1), SOFTWARE ASSURANCE STANDARD

NASA-STD-8739.8 (w/ CHANGE 1), SOFTWARE ASSURANCE STANDARD (NASA TECHNICAL STANDARD - REPLACES NASA-STD-2201-93 DATED NOVEMBER 1992). This standard specifies the software assurance requirements for software developed or acquired1 and maintained by the National Aeronautics and Space Administration (NASA) and for open source software, Government off-the-shelf (GOTS) software, modified off-the-shelf (MOTS) software, and commercial off-the-shelf (COTS) software when included in a NASA system. This Standard applies to use of new and existing (e.g., reuse, legacy, heritage) software products and components. The NASA Software Assurance Standard (hereinafter referred to as the "Standard") supports NPD 2820.1, NASA Software Policies, and NPR 7150.2 NASA Software Engineering Requirements. This Standard is compatible with all software life cycle models (e.g., waterfall, spiral, evolutionary, incremental, package-based), and addresses all software life cycle processes, including acquisition, supply, development, operation, and maintenance. This Standard specifies the requirements for software assurance for use by NASA projects, programs, facilities, and activities. It provides a consistent, uniform basis for defining the requirements for software assurance programs to be applied and maintained throughout the life of that software, that is, from project conception, through operations and maintenance, until the software is retired.

NASA-STD-PO23 (DRAFT), ELECTRICAL BONDING FOR NASA LAUNCH VEHICLES, SPACECRAFT, PAYLOADS AND FLIGHT EQUIPMENT

NASA-STD-PO23 (DRAFT), ELECTRICAL BONDING FOR NASA LAUNCH VEHICLES, SPACECRAFT, PAYLOADS AND FLIGHT EQUIPMENT. This standard is approved for use by NASA Headquarters and all NASA Centers and is intended to provide a common framework for consistent practices across NASA programs. MIL-B-5087B, Bonding, Electrical, and Lightning Protection, For Aerospace Systems had been the basic bonding standard for years before its cancellation by the military. MIL-STD-464, Interface Standard for Systems Electromagnetic Environmental Effects Requirements, superseded MIL-B-5087B for military projects. Electrical bonding requirements make up only a small section of MIL-STD-464, and MIL-STD-464 is not applicable for NASA projects. The intent of this NASA standard is to provide stand-alone requirements and to provide enough data to help modify requirements or to allow waivers if needed. Requests for information, corrections, or additions to this standard should be directed to the Electromagnetic Environmental Effects Team, ED44, MSFC, AL 35812. Requests for general information concerning NASA Technical Standards should be sent to the NASA Technical Program Standards Office, ED41 MSFC, AL 35812, (telephone 205-544-2448). This and other NASA standards may be viewed and downloaded, free-of-charge, from our NASA Standards Homepage: http://standards.nasa.gov.

NASA-STD-PO25 (DRAFT 1), SELECTION OF METALLIC MATERIALS FOR STRESS CORROSION CRACKING RESISTANCE IN SODIUM CHLORIDE ENVIRONMENTS

NASA-STD-PO25 (DRAFT 1), SELECTION OF METALLIC MATERIALS FOR STRESS CORROSION CRACKING RESISTANCE IN SODIUM CHLORIDE ENVIRONMENTS (This Document Formerly Published as MSFC-STD-3029, MAY 2000). This standard is based on MSFC-STD-3029, "Guidelines for the Selection of Metallic Materials for Stress Corrosion Cracking Resistance in Sodium Chloride Environments”. In addition to the information that was in MSFC-SPEC-522B, “Design Criteria for Controlling Stress Corrosion Cracking”, which was originated more than 25 years ago as a tool to control stress corrosion cracking throughout NASA programs, NASA-STD-P025 contains additional alloys in the tables, requirements for the classification of alloys, additional references, a list of the documents associated with stress corrosion research, four additional figures and information on the test methodology.