55 20 8239 https://digitalprojects.uah.edu/files/original/20/10582/satsivcryoweighsyst-II_072007103745.pdf 1be6512f78ca58e0c4ece0b73fa74770 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satsivcryoweighsyst-II_072007103745.pdf spc_stnv_000694 Title A name given to the resource "Saturn S-IV cryogenic weigh system. Part II : weigh operations." Description An account of the resource Two basic methods for mass determination are: (1) direct measurement, (2) volume and density determination. Both methods or variations have been used to determine space vehicle propellant mass with varying degrees of success. Stringent propellant loading accuracy requirements of k0.5 percent for the Saturn S-IV Stage have led to the development of a Cryogenic Calibration Weigh System. The method employs accurate electronic force transducers and measuring systems as the standard and experimental weighings have verified achievement of better than the required accuracy. Creator An entity primarily responsible for making the resource Matsumoto, G. A. Date A point or period of time associated with an event in the lifecycle of the resource 1965-06-20 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Liquid propellant rockets--Fuel tanks--Level indicators Cryogenic rocket propellants Saturn S-4 stage Type The nature or genre of the resource Text Reports Source A related resource from which the described resource is derived Saturn V Collection Box 14, Folder 17 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000675_000699 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17164 https://digitalprojects.uah.edu/files/original/20/10580/satsivcryoweighsyst_072007101249.pdf 17cfd3ced4f9086134a3da162c1067aa Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satsivcryoweighsyst_072007101249.pdf spc_stnv_000692 Title A name given to the resource "Saturn S-IV cryogenic weigh system. Part IV : safety." Description An account of the resource During cryogenic weigh system operation, hydrogen when combined with oxygen can create an unsafe condition. Therefore the concentration of the residual oxygen and hydrogen from leaks in the cryogenic weigh environmental bags must be known at all times during the cryogenic weigh. Hydrogen and oxygen detectors will provide the optimum method for maintaining safe conditions. Hydrogen properties and safe mixtures are reviewed. The method selected to analyze the oxygen content is discussed. The selection, development, and testing of a hydrogen detector system is examined. Creator An entity primarily responsible for making the resource Corcoran, Edward G. Date A point or period of time associated with an event in the lifecycle of the resource 1965-06-20 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Liquid propellant rockets Cryogenic rocket propellants Safety Type The nature or genre of the resource Text Reports Source A related resource from which the described resource is derived Saturn V Collection Box 14, Folder 8 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000675_000699 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17165 https://digitalprojects.uah.edu/files/original/20/10515/Satusivengi_110110145014.pdf 9d5b1e8dd512865c3853bc062a6719e1 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Satusivengi_110110145014.pdf spc_stnv_000749 Title A name given to the resource "Saturn S-IV engines." Description An account of the resource Folder of information. Creator An entity primarily responsible for making the resource Pratt & Whitney Aircraft Company Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Launch vehicles Type The nature or genre of the resource Still Image Photographs Source A related resource from which the described resource is derived Saturn V Collection Box 32, Folder 24 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000725_000749 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/18212 https://digitalprojects.uah.edu/files/original/20/10469/Satusivfirs_102810143053.pdf 47a1bdb01d79f03806635a043908a236 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Satusivfirs_102810143053.pdf spc_stnv_000751 Title A name given to the resource "Saturn S-IV first firing." Description An account of the resource Press release detailing the firing of the Saturn S-IV in California. Creator An entity primarily responsible for making the resource Douglas Aircraft Date A point or period of time associated with an event in the lifecycle of the resource 1962-08-18 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Type The nature or genre of the resource Text Press Releases Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Is Part Of A related resource in which the described resource is physically or logically included. Saturn S-IV engines. Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 https://digitalprojects.uah.edu/files/original/20/10514/satuS-IVBquartechprogrepo_110607103908.pdf ec89715c7c041fbb8ed75639c71cf920 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satuS-IVBquartechprogrepo_110607103908.pdf spc_stnv_000748 Title A name given to the resource "Saturn S-IVB quarterly technical progress report." Description An account of the resource Douglas Aircraft Company Report DAC-56445, Saturn S-IVB Quarterly Technical Progress Report, covers design and development progress on the Saturn IB and Saturn V configurations of the S-IVB stage during August and September 1966. This report is prepared for the National Aeronautics and Space Administration under Contract NAS7-101. Creator An entity primarily responsible for making the resource Rainwater, B. J. Douglas Aircraft Company. Missile and Space Systems Division Date A point or period of time associated with an event in the lifecycle of the resource 1966-09-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles--Design and construction Saturn launch vehicles--Testing Project management Saturn S-4B stage Type The nature or genre of the resource Text Progress Reports Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 5 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000725_000749 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17526 https://digitalprojects.uah.edu/files/original/20/10578/Satquatecprorep_022108133339.pdf 95165ed12e55edf43f345ca94c56cb37 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Satquatecprorep_022108133339.pdf spc_stnv_000690 Title A name given to the resource "Saturn S-IVB quarterly technical progress report." Description An account of the resource Douglas Aircraft Company Report DAC-56533, Saturn S-IVB Quarterly Technical Progress Report, covers design and development progress on the Saturn IB and Saturn V configurations of the S-IVB stage during January, February, and March 1967. This report is prepared for the National Aeronautics and Space Administration under Contract NAS7-01.; Prepared for National Aeronautics and Space Administration under NASA contract NAS7-101.; Approved by A. P. O'Neal, Director, Saturn Development Engineering. Creator An entity primarily responsible for making the resource Rainwater, B. J. Date A point or period of time associated with an event in the lifecycle of the resource 1967-03-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn launch vehicles--Design and construction Saturn launch vehicles--Testing Project management Type The nature or genre of the resource Text Progress Reports Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 5 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000675_000699 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17526 https://digitalprojects.uah.edu/files/original/20/10504/saturnsa-1flighanditsinstrumenta_031607091738.pdf 3a7e47a2a9d4269193f09c9a0e86bd84 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context saturnsa-1flighanditsinstrumenta_031607091738.pdf spc_stnv_000736 Title A name given to the resource "Saturn SA-1 flight and its instrumentation." Description An account of the resource Presentation focusing on empahsising the importance of space programs such as Saturn. Date A point or period of time associated with an event in the lifecycle of the resource 1962-04-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn 1 SA-1 launch vehicle Saturn launch vehicles Astronautical instruments Spacecraft instruments Astrionics Type The nature or genre of the resource Text Presentations Source A related resource from which the described resource is derived Saturn V Collection Box 6, Folder 56 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000725_000749 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16768 https://digitalprojects.uah.edu/files/original/20/10471/SatuST12inerguid_051310124015.pdf 59b9cecf1915a4fd9c82224181eb4ad0 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context SatuST12inerguid_051310124015.pdf spc_stnv_000753 Title A name given to the resource "Saturn ST-124-M inertial guidance platform." Description An account of the resource a press release which focuses around the Apollo 9 flight and what role the ST-124-M inertial guidance platform has in it. Creator An entity primarily responsible for making the resource Bendix Corporation. Navigation & Control Division Date A point or period of time associated with an event in the lifecycle of the resource 1969-02-21 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Lunar module Type The nature or genre of the resource Text Press Releases Source A related resource from which the described resource is derived Saturn V Collection Box 30, Folder 28 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/18078 https://digitalprojects.uah.edu/files/original/20/10583/satstasIIjul71961min_031307092529.pdf 9c4f9f2166f47fe2b5df4afe06e61335 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satstasIIjul71961min_031307092529.pdf spc_stnv_000695 Title A name given to the resource "Saturn stages S-II : July 7, 1961 : Minutes of the phase II pre-proposal conference for stage S-II procurement." Description An account of the resource Transcription of a confrence aiming to propose ideas for new rocket designs. Includes references to slides. Date A point or period of time associated with an event in the lifecycle of the resource 1961-07-07 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn stages Saturn S-2 stage Saturn S-4 stage Saturn launch vehicles Type The nature or genre of the resource Text Presentations Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000675_000699 https://digitalprojects.uah.edu/files/original/20/11097/Satusyststud.pdf 2bb900b88002ede944f200bb13b2f7f2 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Satusyststud.pdf Title A name given to the resource "Saturn system study II." Description An account of the resource Study regarding the three-stage carrier vehicle E-1 engines. Creator An entity primarily responsible for making the resource United States. Army Ballistic Missile Agency. Development Operations Division Date A point or period of time associated with an event in the lifecycle of the resource 1959-11-13 Temporal Coverage Temporal characteristics of the resource. 1950-1959 Subject The topic of the resource Saturn project Saturn launch vehicles Saturn stages Saturn launch vehicles Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collection Box 4, Folder 24 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16591 https://digitalprojects.uah.edu/files/original/20/11104/Sa-203.pdf.pdf 2f23877357766caa4afb305cfc714dea Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Sa-203.pdf Title A name given to the resource "Saturn technical information handbook. Volume III of four volumes : SA-203." Description An account of the resource The "Saturn Technical Information Handbook" provides up-to-date reference material to the Launch Operations Center personnel. This material shows the assembly and operation of the Saturn Vehicle components for systems analysis.; Volume II is available on the NASA Technical Reports Server (NTRS) as a PDF. Creator An entity primarily responsible for making the resource Technical Writing and Handbook Section Date A point or period of time associated with an event in the lifecycle of the resource 1960-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Type The nature or genre of the resource Text Manuals Source A related resource from which the described resource is derived Saturn V Collection Box 17, Folder 11 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000675_000699 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17434 https://digitalprojects.uah.edu/files/original/20/10472/satutelesystforSA-6_032207094948.pdf 56cbebd2298e6994c8686e71fdf2a651 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satutelesystforSA-6_032207094948.pdf spc_stnv_000754 Title A name given to the resource "Saturn television system for SA-6." Description An account of the resource The Saturn television system is an instrumentation device intended to provide visual information on vehicle performance in real time. The system covers the entire problem from the original image presented to the television camera to the presentation of the finished photographs for analyses. Creator An entity primarily responsible for making the resource Huggins, Carl T. Date A point or period of time associated with an event in the lifecycle of the resource 1963-02-25 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicle Television Spacecraft electronic equipment Type The nature or genre of the resource Text Internal Notes Source A related resource from which the described resource is derived Saturn V Collection Box 8, Folder 14 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17311 https://digitalprojects.uah.edu/files/original/20/10490/SatVnsproclauvehgrosuppequip_042108143716.pdf ba5bcfe3e47376e2347d5a395f8d694b Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context SatVnsproclauvehgrosuppequip_042108143716.pdf spc_stnv_000772 Title A name given to the resource "Saturn V : non-stage procured launch vehicle ground support equipment." Description An account of the resource The functions, authority, management relationships, and responsibilities of the Launch Vehicle Ground Support Equipment Project Office are described. Functions and examples of non-stage procured Launch Vehicle Ground Support Equipment (LVGSE) are described and illustrated. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center. Vehicle Ground Support, Equipment Project Office Date A point or period of time associated with an event in the lifecycle of the resource 1967-08-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Ground support systems Saturn launch vehicles Ground support equipment Management Type The nature or genre of the resource Text Design Reports Source A related resource from which the described resource is derived Saturn V Collection Box 23, Folder 30 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17720 https://digitalprojects.uah.edu/files/original/20/10486/satvamemooroc_013008120434.pdf f2df90757d333786a613f13cdb84c7e6 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satvamemooroc_013008120434.pdf spc_stnv_000768 Title A name given to the resource "Saturn V America's moon rocket." Description An account of the resource Diagram that displays the Saturn V rocket with a page beneath detailing the function of each stage. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center. National Aeronautics & Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1967-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Space flight to the moon Manned space flight Saturn launch vehicles Type The nature or genre of the resource Still Image Diagrams Source A related resource from which the described resource is derived Saturn V Collection Box 20, Folder 5 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17588 https://digitalprojects.uah.edu/files/original/20/907/spc_stnv_000010.pdf 10ac3b82dac2dd680af8b5ecb2d1e5dd PDF Text Text � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000010 Title A name given to the resource "Saturn V Apollo Flight Configuration." Description An account of the resource Drawn by Don Sprague at the Huntsville Engineering section of Boeing. Creator An entity primarily responsible for making the resource Boeing Aerospace Company. Space Division. Launch Systems Branch Date A point or period of time associated with an event in the lifecycle of the resource 1967-03-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Project Apollo (U.S.) Saturn launch vehicles Saturn Project (U.S.) Type The nature or genre of the resource Diagrams Still Image Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. This item was digitized for the Apollo 11 50th anniversary celebration. Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource ap11_exhibit_2019_08 https://digitalprojects.uah.edu/files/original/20/10487/satvapoflicon_060508122521.pdf a94d2316bfab4e7dc611af8084120488 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satvapoflicon_060508122521.pdf spc_stnv_000769 Title A name given to the resource "Saturn V Apollo flight configuration." Description An account of the resource Diagram displaying the internal rooms, pieces and functions of the Saturn V as well as the space-suits of the astronauts. Creator An entity primarily responsible for making the resource Huntsville Engineering Date A point or period of time associated with an event in the lifecycle of the resource 1968-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Saturn launch vehicles Space suits Saturn launch vehicles Type The nature or genre of the resource Still Image Diagrams Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/search?utf8=%E2%9C%93&op%5B%5D=&q%5B%5D=Saturn+V+Apollo+flight+configuration&limit=&field%5B%5D=&from_year%5B%5D=&to_year%5B%5D=&commit=Search https://digitalprojects.uah.edu/files/original/20/10488/satvapollunorbitrend_050807104721.pdf 581a71addaf6520a34710d85d773fc7d Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context satvapollunorbitrend_050807104721.pdf spc_stnv_000770 Title A name given to the resource "Saturn V Apollo lunar orbit rendezvous mission." Description An account of the resource Diagram explaining the process of a lunar mission from liftoff to recovery. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1963-09-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Saturn stages Saturn launch vehicles Space flight to the moon Orbital rendezvous Type The nature or genre of the resource Still Image Diagrams Source A related resource from which the described resource is derived Saturn V Collection Box 9, Folder 30 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16857 https://digitalprojects.uah.edu/files/original/20/10473/SatuVDeri_062308104520.pdf 65e8a00304464fbdf8d8a8d8c4a9ff96 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context SatuVDeri_062308104520.pdf spc_stnv_000755 Title A name given to the resource "Saturn V derivatives." Description An account of the resource This paper desciibes an evolutionary family concept of !h turn V derivative launch vehicle systems, discusses their performance capabilities, and outlines their ability to perform orbital and hlgh-energy missions at minimum total program cost. Creator An entity primarily responsible for making the resource Scott, Ronald D. Date A point or period of time associated with an event in the lifecycle of the resource 1965-02-25 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Saturn V launch vehicles Technology Research and development Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collection Box 25, Folder 10 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17818 https://digitalprojects.uah.edu/files/original/20/10474/satuVfirsstagannuprogrepofiscyear1966_091207124644.pdf 7d805789537ed2ae46a5e5185e7ba4fc Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Satuvfirststag.pdf spc_stnv_000756 Title A name given to the resource "Saturn V first stage annual progress report : fiscal year 1966." Description An account of the resource This report is the consolidation of D5-11994, "Quarterly Technical Progress Report," for the fourth fiscal quarter and the fiscal year 1966 Annual Progress Report and places special emphasis on activities on the fourth fiscal quarter. Creator An entity primarily responsible for making the resource Boeing Company. Space Division Date A point or period of time associated with an event in the lifecycle of the resource 1966-07-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Management Type The nature or genre of the resource Text Progress Reports Source A related resource from which the described resource is derived Saturn V Collection Box 18, Folder 1 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000750_000774 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17496 https://digitalprojects.uah.edu/files/original/20/1150/spc_stnv_000066.pdf dc89991be249aab5abf4e1bf6256528d PDF Text Text THE COMP)IIYY/SPCE DIYISION,~AUNCH SYSTEMS BRANCH �ANNUAL PROGRESS REPORT J U N E 30, 1967 THROUGH J U N E 27, 1 9 6 8 CONTRACT N A S 8 - 5 6 0 8 , SCHEDULES 1 A N D 1A J U L Y 27, 1 9 6 8 LAUNCH SYSTEMS B R A N C H SPACE D I V I S I O N T H E BOEllUO C O M P A N Y PREPARED BY SUPERVISED BY D.6. Valentine M a n a w m R w m g and Analysis APPROVED BY APPROVED BY Illlichawl Pmgram Warning and Reporting Manager APPROVED BY �DISTRIBUTION M, L. Alberstadf., Jrr 1 L, D, Alford J* F, Allan W. R. Allen We C, Applegate N. Bender S. Bergeman L, E. Buchart * L, G, Chchraa F. L, Csenen E. IG Cooper D. H. Creim R. T. Crowley W. W. Davis C. H. Donald Re C. Dunigan J. J. Eckle C, E. E n a f t A, A. Geiger H. D. Gunning D. 0. Haas C, W. Harris K i S. ingram J. Irico I, A. Johnson S. P. Johnson H. Kudish S. D. KruU T. R. Marley A. D. Martin C. L. M c h t i r e E. J. Merkel T. M. Mladfneo * J. D. Monroe R. H. Nelson J. L. O1Neil B, L. Osborne J. E. Parazynsld W, H. Quarles H. C. Runkel I%, C, Sanders J. V. Smith T. J. Smith H. L. Smotherman T. P. Snow C. J. Solar J, C. Sormsw D5-12601-6 I 1-1855 5-9000 5-1830 5-3100 5-1800 5-1100 5-1660 5-1910 5-1500 6-8000 5-1900 5-1200 5-7300 5-7900 5-1705 5-1070 5-7400 5-7150 5-8010 5-1070 5-1854 5-3000 5-1910 5-1300 5-1211 5-7200 5-1600 5-5000 5-3200 5-1700 5-1230 5-1230 5-1800 5-1400 5-1000 5-3600 5-1100 5-1430 5- 1940 5-7000 5-1010 5-1020 5-1260 5-9100 LA-42 JA-51 LN-70 LA-35 LA-02 LT-90 LR-69 LD-42 LR-60 FA44 LD-42 LA-19 LS-72 LS-55 LC-23 LA-42 LS-76 LS-23 FA-14 LA-42 LN-54 LA-10 LD-33 LT-43 LT-91 LP-36 LR-65 TA-01 LA-03 LA-23 LD-03 LT-92 LA-02 LN-98 LA-42 LA-18 JB-75 LN-87 JD-2 1 LS-40 LA-42 LA-31 LT-96 JD-5 1 2-5907 Sahara Park 5-1100 LT-90 5-7100 L9-28 R. L, Stallings G, H, Stoner (2) C, D. & C O U ~ R. F. T e ~ r y D, G. Valentiue (10) J. G. Weber C. W. Weteel C, A. WlIWnson L, A. Wood L, Yanolf Michoud Contracts Files Facilities Central Files Program Presentations Library (2) J. Keller 5-5240 5-1000 5-1300 5-1220 5-1220 5-1020 5-1100 5-2000 2-1000 5-1020 TA-03 84-22 LT-43 LA-2 1 LD-59 JB-33 LT-90 RS-O 1 1448 JB-33 5-1100 LT-90 5-1492 LN-95 5-1220 LP-02 1200 Cornmonwedth Bldg, 1625 K. Street, N. W, Washington, D. C. 20006 R. W, Brown M. E. Buchholz A. V. Clark H. S. Garrett J. E. Glazner H, W. Hallisey (2) C. W. Holmes F. W. Johnson T. S. Johnston L. L. Jones J. R. King H. T. Mimey J. W. Moody D. H. Newby W, R. Reynolds M. H. Riley C, L. Thionnet J. B, Taylor R-QUAL-J I-CO-LH R-P&VE-XG MS-D R-QUAL-AE I-V-S-IC R-OM-V I-V-T I-V-P MS-H R-ASTR-BV I-CO-LB I-V-Q DE P-A R-QUAL-QP R-QUAL-PC R-AERO-P I-K-V NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA NASA B. H. W. M. G. N, W, B. I-MICH-C I-MICW-F I-MICH-MGR I-MICH-QES I-MICH-OB I-MICH-DU 11-MICH-QR NASA NASA NASA NASA NASA NASA NASA Aldridge Bailey Constm Herrhgbn R, J, Nuber S, Smith W, L, WiW.ms iii �Summary Michoud Assembly Facility Mississippi Teet Facility; Page No, iii iv DBTRXBUTION CONTENTS ILLUSTXUTIOSS FOREWORD S-IC PfiOCRAM SUMMARY c 1 ,., 0 ' Summary Documentation Support Spares Support Personnel Support Spares for Government Furnished Equipment 1 3 4 8 9 9 10 10 10 10 15 18 19 5 6 - 23 25 30 54 57 63 66 66 81 LAUNCH OPERATIONS Launch Operations S-IC-3 Quality Verification 7 79 81 81 81 STAGE SYSTEMS STUDIES 89 89 ADVANCED STUDIES APPENDIXES Appendix A Appendix B Appendix C Appendix D - Contract Modifications - Proposals Submitted - Negotiations Completed - Deliverable Data Submitted Appendix E - Engineering Change CONTRACT END ITEMS AND SERVICES Summary Deliverable Hardware Design and Engineering Manufacturing Development Quality Assurance Product Performance Assurance New Technology Deliverable Data Q LOGISTICS 4 vf vii PROJECT MANAGEMENT Summary Contracting Activity Program Plans, Schedules and Reports Equipment Management Configuration Management Technical Program Analysis and Review Cost Effectiveness Program Cost Improvement Motivation Industrial Management Computer Sciences Business Information Services Michoud Organization Realignmen& 2 v 69 71 73 Appendix G Appendix F GLOSSARY Documentation Completed During FY 1968 Engineering Changes Initiated During FY 1968 MTF Systems Test Documentation Status 97 97 97 97 98 105 118 120 �ILLUSTRATIONS Page No. Figure 1-1 Figure 1-2 Figure 1-3 Figure 1-4 Figure 2-1 Figure 2-2 Figure 2-3 Figure 2-4 Figure 2-5 Figure 2-6 Figure 2-7 Figure 2-8 Figure 2-9 Figure 2-10 Figure 2-11 Figure 2-12 Figure 2-13 Figure 2-14 Figure 2-15 Figure 2-16 Figure 2-17 Figure 2-18 Figure 2-19 Figure 2-20 Figure 2-21 Figure 2-22 Figure 2-23 Figure 2-24 Figure2-25 Figure2-26 Figure 2-27 Figure 2-28 Figure 3-1 Figure3-2 Figure 3-3 Figure 3-4 Figure 3-5 Figure 3-6 Figure 3-7 D5-128016 Michoud Program Control Center R e p o m d Xnjuriaa in FY 1968 FY 1968 Injuries P e r Million Manhours MTF Document Activity During FY 1968 AS-501 Moving From KSC VAB AS-501 Launch S-fC -F LUX Duct Removal LOX Duct Installed in POGO Test F i x b e S-PC Stage Being Moved From Factory S-IC-7 Stored in Factory Building S-IC-8 in Vertical Assembly S-IC-8 Being Removed From VAB F-1 Engine Installation in S-IC 6-IC Propellant Tank Being Moved From Factory Percentage Complete Major Structures June 27, 1968 S-IC-3 Versus -2 Dry Weight Status Breakdown of S-IC Stage Weights S-IC Power Distribution System LOX Fill and Drain Valve Redesign S-IC Propellant Dispersion System Center Engine Redundant LOX Cutoff Sensor S-IC TV System S-IC Film Camera Capsule Assembly S-IC ODOP System S-IC Qualification Test Summary Growth of Assessed Reliability S-IC Stage S-IC Repair Weld Frequency Quality Audits S-ICRiskAppraisalCycle S-ICQualityMaintenanceProgram Organizational Safety Relationship ~htegratedSafety Program Controlling Documentation Cincinatti Automatic Tooling Center S-IC-5inTestStand S-IC-5 Static Firing S-IC-5 Being Removed From T e s t Stand Couapsed S-IC-6 Fuel Emergency Drain Duct Instalfation d 8-IC-D in T e s t Stand Plexighs Ducts Installed on S-I[C-33 - - - - 6 11 13 20 25 25 26 26 27 27 28 28 28 29 29 30 32 33 34 35 36 40 41 42 48 54 55 60 64 65 65 65 71 73 73 73 74 75 75 v ��F Y 1968 several major Saturn&-IC program milestones, whichwere of utmost importthe ApoUo program's mission of placing men on the moon, were achieved. The most icant milestones reached were the successful launchings of the first and second Apollol V vehicles, AS 4 0 1 and -502, from the Kennedy Space Flight Center, The AS-501 wate ed from K e m d y Space Flight Center at ?:QQ!O1 a, m. , EST, on Navember 9, 1888. -1C-1 and its Boeing Schedule I supplied ground support equipment performed exceedwell during launch and flight. AS-502 lift-off occurred at Kennedy Space Flight Center t 7:00:01, on April 4 , 1968. Performance of all systems on the S-IC-2 and its Boeing Schedule f supplied ground support equipment was satisfactory during launch and flight. However, longitudinaf oscillations (POCO)were experienced during flight. Boeing is expending every effort to alaviate thfe phenomenon in all future S-IC fights. Subsequent to the launch of AS-501 and -502, the decision to make AS-503 the first manned aturn V mission was reached. The first stage for this mission, the S-IC-3, is the Michoud assembled S-IC flight stage. This vehicle was accepted by NASA during F Y and then placed in storage at Michoud. It was later removed from storage, retested, shipped to Kennedy Space Flight Center, arriving there on December 27, 1967. At the s e of the reporting period, the S-IC-3 was at Kennedy Space Flight Center where it is ergoing extensive modification in preparation for the first manned launch. Other significant S-IC program incentive milestones achieved during 1968 include delivery of he 5-IC-4 to the Customer, on-dock Michoud, on August 28, 1967; successful static firing of the S-IC-5 at the M ississfppi Test Facility on August 25, 1967; and successful completion of the S-IC-6 and -7 post-manufacturing static firing readiness tests on July 24 and N o v e d e r 12, 1967, respectively. oeing/'Michoud testing programs were conducted throughout the year with the purpose of resolving design data problems, discrepancies, and anomalies identified during manufacturng , static firing, and AS-5 01 and -502 launch support operatiom. Major testing programs hat were conducted on a continuing basis included the reliability, qualification, development, and failure analysis test programs. Project management techniques, designed to assure efficient and effective management of the S-IC program, were under constant surveillance throughout FY 1968. An S-IC Integrated Safety Program, which is responsive to both Boeing Corporate policies and NASA requirements ,-was established during October of 1967. This program combines and integrates the previously separate industrial and systems safety plans into one overall safety program, and is overseen by the S-IC Safety Board that meets on a regular basis to provide program direction. This arrangement provides for a single safety focal point for increased Management control and improved visibility of safety performance versus assigned tasks, thereby assuring safety excellence in all phases of the S-IC program. t Throughout FY 1968 management reviews, concerning all aspects of the S-IC program, were conducted. Among these reviews were the three contractually required S-IC Technical Progress and Program Reviews that were conducted to inform NASA personnel of Boeing's progress and performance on Contract NAS8-5608. Internal Boeing Management reviews during the year included periodic meetings of the Saturn Performance and Saturn Launch Readiness Boards. These Boards are made up of Boeing executives from affected Boeing/Saturn programs and have as their mission assurance of proper performance of all Saturn contractual obligations. Personnel reassignments and organizational restructuring continued throughout the year with the purpose of assuring effective management of the S-EC program. Of major significance was the relocation -of the Baeing S-IC Systems Test eanagerts office from Michoud to the Mississippi Test Fwility. This relocation was made to enhance the coordination between Boeing Manageme* ar$ W NASA Missiesippi Test Facility Management. DS-12601-5 vii ��b SUMMARY Project Management activities during the year were directed toward managing the S-IC program to assure optimum utilization of resources and the attainment of sfa;nliic& Bllllestones including ail contractudly roquLPed obUgstiolup. During BY 1968 long-lead procurement for stages S1C-16 aod -17 was initiated under Contract NASB19644. This contract was executed on July 25, 1967, Urnfaate$ 3 the convrraienca, of *.he g o v e m e n t an Octotrer 18, 1967, and rs-at@ld an Mmoh 8, 1968. Because S-IC stages were being produced at a greater rate than they could be effectively utilized, revised program schedules and guidelines were received during the year, Boeing agreed to these revisions subject to an equitable adjustment to the Contract, and on November 13, 1967 Supplement Agreement 1MICH662 formally placed the Apollo Program 4.H schedule on contract. Negotiation of MICH-662 began on June 17, 1968 arid was continuing at the end of the reporthg mria, aft,J w 14, ti368 S ~ p g t b ~~ sg !n~v ~UId Apallo Pram= 43 meat. 977, wkfch c Schedule, was received from NASA. Negotiation of this new schedule wLU begin "immediately following" completion of MLCH-662 negotiations, The Michoud Cost Effectiveness Program was established during the reporting period. Activities under this program are directed toward identifying, evaluating, i~ndimplementing ckangea that reduce t;he total cost of the S 4 C stage and derivatives. The Michoud Cost Improvement program also continued to operate effectively throughout the year with a reported validated cost savings of $14,200,788 as compared to a goal of $9,585,740. The Boefngmfofisud work; foroca u d e m e n t adljusrtments during this fiscal year to compensate for the reduction in activity resulting from schedule slides. The work force reporting to the Boeing/Rlichoud manager was reduced by 833 which resulted in a total workforce of 4254 at the end of the fiscal year. Various Boeing/Michoud personnel were also placed on loan to alleviate manpower problems at other Boeing Saturn locations, Efforts were made to assure that Plans for Progress and Equal Employment Opportunityprograms continued during the repnrtiw prlod. Ao a part d %& g ~ e parrn an Equal Employment Opportunity Adminiskation function and aa Equal Employment Opportunity Committee were established to promote equal wPOm@* * D5412601-5 1 �CONTRACTING ACTIVITY CONTRACT DELIVERY SCHEDULE During 1967, it became increasingly apparent that S-IC stages were being produced at a rate greater than the ApoUo Program could effectively utillse. On SeptemSer 1, the NASA Contracting Officer gave official recognition to this fact by a letter requesting immediate implementation of certain "revised program gutdeliine8." On September 12, Boeing agreed to proceed with a revised plan subject to an equitable odjatment of the contract. an November 13, Supplemental Agreement FA) MICH-662 formally placed the new 4H Schedule on contract. the Saturn S-IC program. The requirements for such equipment are established by program needs and submitted to the government in the form of a fiscal year plan. The forecast is negotiated and the necessary level of funding is placed on contract. During FY 1968, funding of the facilities contract was increased in the amount of $930,000. CONTRACT MASS-5608 (SCHEDULES I & AND IA) During this reporting period, the following schedule and performance incentive milestones were accompll~bedunder Srihedule I of the constract: July 24, 1967 Successful completion of the S-IC -6 stage post-manufacturing static firing readiness test for full (299.6) incentive points O n June 17, 1968, negotiation of the 4H Schedule (SA MICH-662) was initiated based on cost proposals submitted in February and March 1968. Both parties have agreed to negotiate the further impact of SA 777 "immediately following' the conclusion of the SA MICH-662 negotiation. August 25, 1967 Successful static firing of the S-IC-5 stage for maximum (260) incentive points August 28, 1967 Acceptance by the Government of the S-IC-4 stage for 3494.6 out of a possible 3498.6 incentive points NASA PROCUREMENT REORGANIZATION For the above milestones, a total of 4,054.2 of a possible 4,058.2 incentive points were earned. In early 1968, informal conversations with NASA/ Michoud contracting personnel indicated that the procurement function for S-IC stages would be moved to MSFC in Huntsville, Alabama. This was done on April 1, 1968. A s a result, Boeinghlichoud Contracts has established and staffed the "Huntsville Representative" office to maintain li*$son with the NASA procurement function. The transition has been made without major perturbations, and it is believed that, other than the increased travel by Boeinghlichoud Contracts personnel, no impact will result. November 13,1967 Successful completion of the S-IC -7 stage post-manufacturing static firing readiness test for maximum incentive points. The incentive points earned on this milestone a r e being held in abeyance pending revision of contract schedules and incentive arrangements in accordance with SA MICH-662. A further schedule slide identified as 41 was contractually implemented by SA 777 on June 14, 1968. CONTRACT NAS8-5608 (SCHEDULE 8 ) CONTRACT NlANAGEMENT CONTRACT NAS8-2577 I n a letter dated February 1, 1968, NASA formally acknowledged accompii8hment of the performance requirements and administrative actions necessary to close out this contract. F M payment was received on F e b r u a y 5, 1968. CONTRACT NAS8-5606(F). This contract covers special facilities equipment for 05-1260 1-5 On February 15, 1968, Schedule IB to Contract NAS85608 was established for the purpose of providing documentation, modification kits, and parts to support the S-IC-T stage and the Systems Development Facility Mechanical Automation Breadboard (MAB. The new schedule was fully funded in the amount of $170,000. CONTRACT NAS8-17218 The technical work statement has been completed. To effect contract closeout, letters of cerfification and dher eoidence of contract completion are be- �ing provided to the Contracting Officer. CONTRACT NAS8-19528 The technical work statement has been completed. In order to effect contract closeout, letters of certification and other evidence of contract completion a r e being provided to the Contracting Officer. CONTRACT fU&8-19544 " TNs contmct for the procurement of long-lead items for owgee $-IC-16 ssd -17 was e x e c ~ t e don July 21, 1967. Nottce af TerminaUon fsr the conv@ntanc@ sf the Government was received from NASA on October 16, 1967. A 11 organizations, including Seattle and Wichita , reported work stopped within the required five-day period. On February 21, 1968, Boeing was informed that NASA Headquarters had approved reactivation of Contract NAS8-19544, SA No. 2 , received (fully executed) on March 8,1968, officially reinstated the contract. This SA provided for: a) Cancellation of the Notice of Termination; b) Reinstatement of the long-lead effort previously authorized by the contract; c) Adjustment of the contemplated delivery dates for stages S-IC-16 and -17 to July 1, 1971, and January 1, 1972, respectively; and d) Extension of long-lead effort through July 31,1968, with provisions for negotiation of a monthly extension toMarch 31, 1969. CONTRACT ACTIVITY fY 1968~ A summary of contract modifications, proposal^ submitt&, negotiations completed, and deliverable data submitted a r e s e t forth in Appendices A , B C and PROGRAM PLANS, SCHEDULES AND REPORTS PROGRAM SCHEDULES Document D5-11040-5, "Launch Systems Branch S-IC Project Contractual Schedules," superseded D5-110404 and was published during the previous reporting period (June 13, 1967). This document outlines the LSB S-EC project eontract schedule for stages 8-IC-3 through -15 a s set forth in CPIF Contract NAS&*5&08 (Schedule I and IA), and S-IC Stage Development and Delivery Plan, MA -2 Schedule, Plan VQIA , which is published by the NASA/MSFC S-IC Project Office. This schedule data establishes the contractual parameters for development of LSB S-IC Plan VIIIA Internal Working Schedules. During FY 1968, one revision was made to D5-11040-5. This revision adjusted contract schedule milestones on S-IC-3, S-IC-5, S-IC-6, and S-IC-7 as directed by the customer and added the period of performance for procurement of long-lead items authorized by CPIF Contract NAS8-19544 for S-IC-16 and -17. Document DS-12695, "8-IC P ~ o g r m Reporting Milestones ," identifies and provides schedule dates for the S-IC program milestones used by Boeing in reporting the progress of Contract NAS8-5608, Schedules I and IA , to MSFC. The milestones s e t forth in this document were established through mutual agreement between Boeing and MSFC to establish a common reporting baseline by which program progress could be measured. Revision "L" to D5-12535, released October 31, 1967, (1)incorporated a revised format, (2) added reference milestones for MSFC produced stages (S-IC -T , S-IC -1, and S -1C -2) and the dynamic test stage (S-IC-D) , (3) added reporting milestones for stages S-IC-11 through -15, and (4) deleted reliability and logistics program reporting milestones. In accordance with revised reporting frequency from "as required" to "once every two months ," three additional revisions, "M ," "Nl1 & "0, It were prepared and released on December 2 1, 1967, February 28, 1968, and April 22, 1968, respectively. Revision "M" and "0" incorporated minor schedule revisions and added actual completion dates for closed out milestones. Revision "N" implemented a completely revised interim schedule, in lieu of a negotiated contract schedule, based on required on-dock Michoud delivery dates contained in Supplemental Agreement MICH-662. Revision "P" is presently being prepared and is scheduled for release during July 1968. This revision will update the interim schedule to be compatible with the internal working schedule released ~ u n e17, 1968. ,. ~5-1.3595, .S-IC ,urn- round Equipment Schedules serves a s an instrument of agreement between MSFC and Boeing on the requirements for and utilization of turn-around equipment a t the Michoud Assembly Facility, Mississippi Test Facility, Marshall Space Flight Center, and Kennedy Space Center. Turn-around equipment,is defined a s those major items of equipment, regardless of complexity, that a r e reused in the assembly, handling, testing, and tramporting of S=-IC stages, Revisions "C" and "I)" to this document were released July 31, 1967 and Maroh 6 , 1968, re- �sptlctively. Both were complete revisions realigning turn-around equipment utilization requiremenis k, be compatible with revised stage internal working schedules, LSD S-IC Internnl Wqrking Schedules, released by Program Letter through tho 8-1;C Program Executivets office, are fssued to establfsh real-time schedule milestones and organizational work interfaces to ensure stage production and test continuity. Three revised working sehedules (schedule No. 's 103, 104, and an interim schedule pending negotiation of a posrlbtr! eehocluic No, 106) ware! reIeased during this raporting pe~lod, Working f3ekedtile Na. 109 was relensed, July 3, 1967, to reflect revised end-item delivery requirements for S-IC-5 and -6 and adjusted schedule dates for completion of PMC for S-IC-7 in accordance with negotiated schedule changes. Working Schedule No, 104 was issued January 5, 1968 to reflect internal schedule realignment necessary to eupport the revised delivery requirements for stages S-IC-3 through -14, which were contained in Supplemental Agreement MICH-662. Arm interim working schedule was published May 28, 1968 to provide transitory schedule direction pending negotiation of a revised delivery schedule. MICH-662 delivery requiren e n t s were invalidated by customer issuance of stop work orders on S-IC-5 and -6. PROJECT PLkN Document D5-11960, Revision D , 'IS-IC Stage Project Management Plan," published in June 1967, presents a sununary view of the organization, planning, and methods used by the Boeing Launch Systems Branch t o provide the most effective means of completing the S-IC project within the schedule and cost g o d s established by Contract NAS8-5608, Schedules I and IA, The contractual requirements for a semi-annual updating of D5-11960, during this reporting period, were changed to an "as-required" basis by Supplement Agreement MICH-310. ings which are held bi-weekly. PERT computer printouts are also forwarded to designated representatives in each affected organization. k number of new innovations have been adopted that reduced the manpower required to support the current level of reporting effort. The major changes included. a) The substitution of Saturn Apollo Reporting Procedure (SARP) charts with a form cover letter for formal bi-weekly reports to the customer; b A $et ~f trend ohart@and a s b z t fel~llf~1e of major prsbleme, that are displayed in the Status Display Center (see Management Control Centers , page 6) were adopted instead of a formal bi-weekly report to Boeing management; and A computer program was developed to automatically construct logic networla from the biweekly master PERT tape. These networks, produced for approximately $. 05 each, provide a graphic image of the computer tape. This greatly reduces the human e r r o r and time required to maintain a history of program accomplishments. MANAGEMENT CONTROL CENTERS The Boeing Program Controlcenter (PCC) (Figure 1-1) provides management with current status of S-IC program schedules, events, and items of concern. The items displayed assist management by depicting the status in a concise manner for rapid comprehension. Among the many changes to the PCC which resulted in increased effectiveness was the installation of ultraviolet lighting during FY 1968. Fluorescent materials are used along with the lighting for vivid portrayal of schedules, event sequences, and other items displayed to aid management. During FY 1968, an area ofthe PCC was devoted toResources Status. Items displayed included manpower, long-lead procurement and budget status. This coverage of resource items will continue to aid in planfuture program activities. ning PROGRAM ASSESSMENT AND PERT SYSTEM The Saturn V/S-IC Launch Systems Branch PERT System report presents milestone status measured against the currently apprwed plan. This report is produced bi-weekly. Items that a r e behind schedule are identi- . fied by t&e PERT system and are called to the attention of management thrwgh PERT assessment meet- The Boeing Status Display Center (SDC) was utilized in FY 1968 to provide real-time tracking for management visibility of stage and GSE open items prior to the launch of S-IC-1 and -2. The viewgrkphs displayed in the SM: were also used to provide the latest S-IC status during the Stage Managerrs Pre-Flight Reviews, the Program Manages's Pxe-Flight Readiness Reviews, MSFC Pre-Flight Reviews, Launch �Readiness Reviews, the Apollo FIight Readiness Reviews, Launch Readiness Board meetings, and other reviews held a t MSFC and BATC The information on the viewgraphs was also transmitted to BATC to inform them of the latest status of hardware for retrofit changes. The status of the S-IC-3, -4, and -5 and associated GSE , MTF , Mechanical Automation Breadboard (MAB) and PERT delinquency status i s currently displayed in the SDC. . The Miehoud Morning Report is published daily to augment the S-IC program information that i s displayed in We P C P and SDC and to inform management of the significant events occurring a t Michoud. . The Management Information Center was established in August 1966 upon completion of the "In-Depth Analysis" of the Michoud organization. This study was initiated to provide an assessment of individual skills and organizational structuring against tasks to be performed. This data is maintained on a current basis and displayed in the Management Information Center= Another important use for this center is the availability of comprehensive personnel data and special display material applicable to equal employ- . ment opportunities. These displays have been reviewed by visiting personnel from the Equal Employment Opportunities Commission and have proven fruitful in assuring the commission of Boeing respo'nsiveness to equal opportunities for all employees. 6 . MANAGEMENT' REVIEWS TECHNICAL PROGRESS AND PROGRAM REVIEWS Customer requirements for S-IC Quarterly Reviews were reducedfromfour tothreeberyear inFY 1967. This requirement remained constant for FY 1968. The 18th, 19th, and 20thS-IC program reviews were conducted inFY 1968. The 18th Technical Progress and Program Review was held at Michoud on July 26, 1967 and reviewed the status of S-IC stages and related activities, particularly S-IC-1 flight readiness. Technical problem r e views covered the need for test data on the characteristics of the Slow Release Mechanism and its effect on AS-501 l&unch, environmental control system incompatibility, and potential stage and GSE changes. The 19th Technical Progress and Program Review conducted at Michoud on December 14, 1967 concentrated on AS -501 (S-IC -1/GSE) prelaunch and flight performance. Anomalies that occurred during prelaunch and flight were discussed and recommendations were made for a number of S-IC instrumentation modifications necessary to obtain technical performance data On subsequent flights. Other problem areas reviewed included configuration differences between S-IC-1 and -2, qualification tests and certifications remaining and the reliability test program. The review ended with a discussion on how configuration management might be improved between Boeing and MSFC . The 20th Technical Progress and Program Review was held at Michoud on June 6, 1568. Major items D5- 121101-5 �covered in the meeting were S-IC-2 Pre-Launch and Flight Performance, and significant preflight and flight anomalies, with emphasis on the LOX vent and relief valve position switch and POGO. Other imporkant items reviewed were S l C - 3 manned eonfiguration c h a m status, S-IC stage distributor rework plan aad schedule, &st and retest quality verification program, and a discussion on the pragrammed reduction of critical skills in Engineering and Operations. SATUW PERFORMANCE AND LAUNCH READINESS BOARD MEETINGS As a part of the Boeing p r o p = tn assure pvoper performance of all Saturn contractual obligations, the Saturn Performance and Saturn Launch Readiness Boanle met periodically throughout F Y 1968. These boards, the membership of which consists of Boeingexecutives from affected Boeing/Saturn programs, hsve as their purpose and scope: a) sult of these conclusions, the following action items were assigned to Boeing Schedule I, and these items have been accomplished to the extent possible at Ohis time: 1) Identify failure modes resulting in vehicle loss and provide the rationale for the acceptability of these risks. 2) Establish the plan and schedule for the elimination of these critical failure modes in support of the first manned ve-bhle. 3) Identify the failure modes that result inlamch scrub o r delay and provide for the elimination of these or the rationale for their acceptance as risks. , 4) - Saturn Performance Board examine the activities of The Bueing Company that provide assurance that the Saturn V launch vehicle will perform in accordance the contract performance requirements and the expectations of the customer, The Board i~iresponsible for initiating corrective action as necessary to assure performance adequacy. b) Saturn Launch Readiness Board - examine the activities of The Boeing Company leading to the preparation of a successful launch of each Saturn V mission. This Board initiates corrective action, where necessary, to assure the maximum effeeUveness of Boeing's overall participation in the Saturn V launch program. The Saturn Performance Board met six times during b) A pre-launch review of Boeing AS-501 and 502 launch critical problems, assessment of the impact of these problems, and assignment of necessary corrective actions. c) Identification and assessment of the adequacy of those activities that represent the unique requirements to qualify Boeing contracted hardware and test operation for man-rating a specific Saturn mission, including: 1) Identfffcation of essential requirements that must be met to provide confidence in manned mission success; 2) Determination if these requirements can be assured by documented analysis and test; and 3) Determination if the evidence of accomplishment can be accommodated in the Design Certification Review written and oral reports. FU 1968. Some of the topics discussed at these meetings were: a) The Board reviewed the design, modification, and test programs associated with S I C pneumatic equipment. As a rerult of this seview, the Board concluded that although this equipment had successY fully (without significant delay) supported 20 static firings of the S-IC, it would be required to operate unattended at KSC for long periods of time (4 to 14 hours) and therefore provided the risk of potential launch delay as a result of component failure. The Board further concluded that there were several failure modes for this equipment that could result in the loss of a stage at MTF o r a vehicle at KSC, and that there were many faflure modes that could result in delaiy a t l m c h scrub at KSC, As a re- Mentify the action necessary to make MTF safe, i. e, , so it is not possible to lose the stage through a failure of this equipment. During FY 1968 the SaturnLaunchBeadiness Board met eight times. Discussions at these meetings included: a) The POGO effect experienced during AS-502 launch and POGO history, possible suppression systems and solutions in work. b) Mscuseion and disposition of AS-501 and -502 prelaunch open-work itemsc c) A r e a of unsatisfactory or marginal performance �EQUIPMENT MANAGEMENT during the AS-501 flight wcre reviewed with the purpose of preventing recurrences during launch of the AS-502. OTHER MANAGEMENT REVIEWS hrrfng F Y 1968 Boeing/Michoud orientation and activity reviews were given to many visiting dignitaria. A synopsis of same of these reviews follows: B a) On October 10, 1967 a briefing was conducted for the Sub-Committee f o r NASA Over-Sight, U. S. ftourss of Reproeenativee (liesiqucr Committee). At this revicw, the sub-committee was briefed on trill Boeing/Sahrn V Apollo activities, including Contract NAS8-5608 schedules I, IA, I1 and Ill, the Apollo Technical Integration and Evaluation contract (NASW-1650f, and New Technology disclosures, Schedule I and LA participation in this briefing consisted of a review of CY 1966 and 1967 schedules, costs, and problems and a preview of anticipated CY 1968 activities. These reviews brought out the fact that Boeing Schedules I and LA a r e underrunning estimated costs, and that the S-IC production program i s well ahead of the contract delivery schedules and Saturn V launch schedules, thus resulting in the necessity to place completed o r partially completed stages in storage. Boeingls transition to this reduced activity and the resultant decreased manpower needs were also reviewed for the committee. A review of the complete Boeing presentation to the sub-committee ie available in the study prepared f o r the Subcommittee on NASA Oversight, entitled "Apollo and Apollo Applications, I f dated February 26, 1968, e b) A short S-IC program briefing was given April 22, 1968 to Dr. Thomas 0. Paine, the then newly appointed Deputy Administrator for NASA. He was accompanied by Dr. Wernher von Braun, General OIConnor, and other NASA representatives. They were also given a tour of MTF and Michoud (NASA, Chrysler, and Boeing). c) On June 6, 1968 a review of the S-IC program was given by Dr. H. E Newell, Associate Administrator for NASA. The presentation explained Boeing's requirements and major rolls in the Saturn V/ApoUo Program, Boeing Space Division organization, a general S-IC stage assembly orientation, and cost performance for Schedules I and LA. The S-IC stage delivery schedule and factory utilization were also dis- cussed. Fallowing the presentation, Dr. Newell was given a plant tour. . a , During FY 1968, the Equipment Management Organization systematically re-evaluated all of its organizationaf functions and responsibilities to determine if certain organizational tasks were still required and if required tasks a r e being accomplished in the most efficbnt manner. Equippent management activities for the year included: a) The "Associated Contractor Liaison Plansffcontract document IN-I-V -S-IC -66-3, equipment management supplied the Marshall Space Flight Center with five data deliveries, including weekly inputs on S-IC equipment acceptance testing. This material will be used in the subject plan; b) "Rocketdyne Requests For Boeing S u p p ~ r t con,~~ tract document IN-I-V-S-IC -65 -9-Rocketdyne requests for Boeing support increased during the reporting period. Ten Rocketdyne requests were received and all were processed; a) Control of operating agreements-Action was taken by equipment management to convert all Boeing Schedule I/Schedule II operating agreements to standard command media. Schedule I / Schedule IlI operating agreement activity continued during FY 1968. This activity increased prior to and after the launch of AS-501 and -502. Schedule I/Schedule ILI operating agreements were reviewed and updated to correct discrepancies and to cover additional needs that became apparent during launch support. Four new operating agreements were established; d) "Master Equipment List," Document D5-12888Equipment management reviewed requirements for ground support equipment, manufacturing support equipment, and all additional equipment. * The master equipment list and all associated documents were revised and updated. The purpose of this review was to determine new equipment requirements and to ensure that all deliv.ered equipment was listed in the document. The result of this study was to provide an accurate and up-to-date listing of Launch Systems Branch S-IC equipment Pequiretnents. A n ad- �ditiond study was made to reduce document frequency md distribution. A s a result, the master equipment list and associated document publications were reduced by 532 per year; B) "Covermont Fumshed Property," (GFP) Document D5-11044-1-TO eliminate duplication that existed due to the publication of two C FP documents; D5-11044-1 (Boeing, and IN-I-V-S-IC-66-1 (contractual], the Equipment Control Board elected to cancel the Boeing CFP document and rely on IN-I-V-S-IC-66-1 as the all-inclusive GFP document. This single document now contains all firm, preliminary, and loaned NAS8-5608 government equipment. During FY 1968, 30 new requests for GFP were reviewed and coordtmted by the Esuivment Con- trol Board, These requists were coordinated with NASA and all equipment has been received by the requesting Boeing organizatiosls. The control board also processed 24 GFP reallocations during the reporting period; and Equipment Control Board-All procedures that define the operation and authority of the Equipment Control Board were reviewed and modernized. One of the objectives of this review was to assure more effective control and reaction time on reallocated equipment. A fast reaction task force was established to accomplish this objective. Controls were also initiated to follow up on reallocated equipment, CONFIGURATION MANAGEMENT Implementation of Program Directives 44 and 44A, to certify stages S-IC-1 and -2 and their associated GSE prior to launch, was accomplished during the year. Certification of the S-IC and its GSE , as directed by Program Directive 44.4, was underway at the end of the fiscal year for a more thorough description of activities required by Program Directives 44 and 4 M , see page 66. Implementation of the requirements of Change Order MICR-633 (Master Installation Notice Card Implementation Program) has been accomplished. This requisement was a prerequisite to proper implementation of that portion of MSFC/KSC Program Directive 448 that pertdm to our certification of the W F C "Saturn V Configuration Index and Modification Status Report" prior to launch of any stage. MICH-770, which has the same intent as MICH-633, has superseded MICH-633, Implementation of MICH-770 had been completed. During FY 1968, limited Product Revision Records (PRRts) were implemented to correct minor engineering deficiencies on delivered but uninstalled retrofit kits. Strict control over the release of these PAR'S is maintained by the configuration accounting office. TECHNICAL PROGRAM ANALYSIS AND REVIEW In February 1968 the new office of Technical Program Analysis and Review was established under the S-IC Program Executive. The purpose of this office is to analyze current management and operational control systems and interfaces with the goal of significantly increasing the effectiveness and efficiency of their performance in supporting program management decision processes. During F Y 1968, two task force efforts were conducted by this new office with the aim of improving the effectiveness and efficiency of stage transfer and delivery, and paperwork circulation at Michoud. The following results were achieved with an estimated net cost reduction of more than $10,000 per stage: a) TO level office labor peaks that occur at stage transfer and delivery, three steps were taken: 1) Changes were initiated against the mechanized as-built data system to minimize effort required to resolve configuration exceptions; 2) A team composed of representatives from the Boeing/Michoud Quality and Reliability Assurance, Operations, and Systems Test organizations was established for Ule purpose of resolving canfiguration exceptions via a procedure that eliminates duplicate effort and shortens flow time; and 3) A factory area was s e t up to perform intermediate staging of "J" (flight) eonfig- �MiCHOUD CENTRAL SAFETY BOC\RO and severity rates of disabling injuries per million manhours worked are represented in Figure 1-2. During FY 1968 the NASA Emergency Evacuation Plan, M-1-29, was published and the Michoud Cen-. tral Safeby Board Chairman, directed each Michoud ccmtr8ctor1s Heath and Safety office to eurvey their wsasr far compliance with this plan, As rr, result of the Boeing survey, thirteen specific recommendations were made, primarily in the Building 102 south mezzanine area, to improve the location and condition of exit signs in the factory . A comprehensive survey was taken of those areas u#- Uziw Pyr-A-Larm fire and smoke dctttsctbrs which contain small amounts of radioactive material. All such detectors were identified and registered with the Louisiana Board of Nuclear Energy, -- MICHOUD LlNE CONTROL SAFETY COUNCIL The Line Control Safety Council continued its activities in safety awareness and accident prevention programs. During the reporting period, recognition for outstanding safety participation was given each month to an individual employee who was chosen by the Council. Additionally, a letter of commendation was written each month to the organization m q e r of the Safety Director who was most effective in promotion accident prevention. LlNE CONTROL SAFETY PROGRAM SUPPORT . The Michoud Safety Training Program gained impetus by the addition of a Safety Indoctrination Course series. This six course series covers safety command media, accident causes and prevention, and specific job hazards. All maintenance and manufacturing employees have attended each course in the series. The Line Control Safety supervisor and the Line Control Safety monitor training courses were updated during the fiscal year and presented monthly, Michoud new hire safety orientation includes instructfon on industrial hazards, Company policy, and command media. Participation in the Line Control program is continually monitored. The "Line Control Program Supervisor's/ Safety Guidewhas been revised and distributed to all supervisors in the Line Control Program. - SAFETY ADMINISTRATION There were 1262 reported injuries in FY 1968 compared to 1625 reported injuries in FY 1967. Health and Safety processed 97 Workmen's Compensation claims in F Y 1968, 8 of which were disabling injuries, This compares ta f27 claims fn FY 1967, 10 of which were disabling injmies, The monthly frequency D5-12601-5 Figure 1-2 Reported Injuries in FY 1968 The statistical injury indices for FY 1968 are compartable: ed to FY 1967 rates in the foUFY 1968 FY 1967 Reported total injury frequency average rate 0'83 Disabling injury frequency rate 0.98 Disabling injury severity rate 20.24 180 1.11 18.2 Workmen's Compensation claim rate 11.9 14.0 *All ratee are per million manhours worked, 11 �A program for inrlrroving the evaluation of crnployees for high risk, high v:liue jobs has been proposed, This program involved revising tho existing certification p r o g r m and providing additfond supervisor training and b?.tfdn$We. I n adtiition, a new combined certificntion and ltcalth csmination progr'm will be administered to provide s standard health examination to all employees engaged in critical tasks. NOUSTRNL HYGIENE AND RADIATION SAFETY Znriustrial hygiene activities d u r i FY 1968 consisted primmay of cvnluntign nrrd control of: emfromental health hazards resulting from fndust~ialoperations. Specific accotnplishments during the past year include the following: TECHNOLOGY AND AUOIT A Health and Safety technology audit function has been formed. This function includes industrial hygiene, radiation safety, safety audits, artd speciai projects. The safety audit program schedule was accelerated to achieve the goal of performing an audit of each shop area every six months, Audit emphasis has shifted from detailed area safety inspections to evaluation of the Line Control Safety Program, and the effectiveness of each organization's hazard identification and conk o l meoaures. PARTICIPATION IN LOCAL INDUSTRIAL HYGIENE AND SAFETY EFFOR?S a) Improved exhaust ventilation was obtained to reduce the exposure to toxic and irritating vapors in the silk screen room and the potting and molding facility; b) A central dust collection system was ob- t a e d for the tool grinding shop, and all equipment in the shop was provided with local exhaust ventilation; During the reporting period, several lectures were presented to classes at Delgado College and Tulane University, and a class of graduate students in environmental health fromTulane were given a lecture and a tour of the Michoud Assembly Facility. c) All changes to process specifications were reviewed to determine that adequate instructions were included conoerning safety handling of hazardous materials; and The New Orleans office of Civil Defense presented a ten-hour Civil Defense Radiological Monitoring Course to selected Michoud personnel. Seventeen Boeing employees completed the course. d) Noise surveys were performed in several areas of the Michoud Assembly Facility, including the carbon arc gouging operation in the manufacturing development laboratory. SAFETY ENGINEERING * A summary of FY 1968 radiation exposure levels for several groups of radiation workers is given below: Number of radiation workers on program 34 Average exposure to all radiation worke r s (millirem) 25 Active support of industrial hygiene activities in New Orleans colleges, universities, and professional societies has continued. Emphasis on hazard analysis and safety design review has been maintained in the areas of manufacturing process changes, test systems, tooling acquisitions, and facility modifications. Functions requiring special attention in the planning of safeguards were the oxygen flow tests, titanium machining, fuel tank hydrostatic test cycling, ablative coating, helium bottle changeout, "POGO" test program, hardware or stage transportation, and steel handling ring installation. SAFETY SURVEILLANCE , Average exposure to a l l quality radiographers (millirem) 33 Average of health and safety monitors (rnillirefn) 53 The maximum allowable dose of radiation, as stated in Louisiana Radiation Regulations, is 5000 millirem per year. The employees on the radiation control program are engaged id welds-x-raying, laboratory work, radiation monitoring, and instrument, calibration. Engineering surveillance and inspection activities have been expanded to provide direct technicd support to the shop safety organizations. Professional safety personnel have been assigned to each shop area to assist in the identification of shop production groblems. This method has proven to be effective. MISSISS1PPI TEST FACILITY HEALTH AND SAFRY ~oeing/MississippiTest facflity completed FY 1968 ' �without a disabling injury, A total of 884,399 manhours were recorded during this period. Boeing/MTF has worked 2,061,972 manhours and recorded only one such injury. That injury occurred in May, 1966. S h e that date 1,89B,6 17 manhours have been worked without a dissblfng injury, The monthly rate of fnjurfea per a9il;lion mmboure worked at MTF ars presented in Figure 173. TOTAL INJURIES January and May 1968. Each of these inspections indicated that our security procedures and Industrial Security Manual compliance are satisfactory. Representatives of Factory Mutual Insurance and Factory Xnsurance Association conducted recurring larss preventton inspections on a quarterly bmis during 1968. These inspections revealed that Boeing fire prevention procedures were satisfactory. A security eduoation program was given to L80 memk bars at mwgrmsnt Iry the Paew Qollrpora%Bimatm of Security on March 25, 1968. Security clearances were granted to 459 employees during FY 1968. tX, J 0 I =r" gm -I d Evacuation control plans were developed for Boeing areas in the S-IC test complex, S-IC booster storage building, and Engineering and Administration Buildings at MTF Evacuation routes were posted in all work areas of these facilities, and detailed instructions were distributed to all personnel. Fire and evacuation drills have been conducted and assessed by management in each facility. Fire brigades were formed and trained for each facility consisting of four teams in the S-IC static test stand and one team in each of the other facilities. -- occupied a 3 . B W .D 9 I : s Figure 1-3 FY 1968 Injuries Per Million Monhours MTF - Several studies have been made to improve fire protection capability on the S-IC Test Stand. These studies have resulted in a proposal that, when implemented , will provide auxiliary fire protection capabiIity when the high-pressure industrial water system is out of service. In August 1967 the Michoud Safety Contest was expanded to include Boeing activities at MTF. Out of a possible 100 points, the MTFts point standing rose from 63.1 to 98.7 by the end of CY 1967. At the end of the fiscal year, Boeing/MTFfs point standing is third with a cumulative standing of 600.5. An MTF quarterly Safety Award Program was established in April 1968, This award is presented to the employee who has demonstrated outstanding safe-work attitudes, influenced the safe-work attitude of fellow employees, taken Mtiative to locate, identify, and report safety hazards, and measurably contributed to the Safety Program. sECURw Proper security of all classified data, matsrial, and hardware was maintained during FY 1968, Security inspections of the Boeing pcrrtiw of the Michoud Aasembly Facility were conduoaed in SepWmber 1967 aad DP-1260 1-5 The Hurricane Preparation Committee conducted a comprehensive review of our existing "Hurricane and Tropical Storm Plan," and although the content of the plan required no changes, there were sufficient organization, location, and title changes necessary to require ib reprinting. The "Boeing/Michoud Plant Disaster Plan," which is a comprehensive disaster control plan, has been updated and released. I t contains detailed planning for the protection of personnel and plant during natural disasters, major accidents, and civil disturbances, also a civil defense and evacuation plan. PERSONNEL MANPOWER Michoud and the Mississippi Test Facility employment declined by 833 employees during FY 1968. This planned reduction was made possible by incrieaafng efficiency, schedule changes, and tke continuing transition from a developmentalto a production type program. The following comparison indicates the reduction in each payrok 13 �T O W Michoud,and MTF 6-29-67 6-27-68 Hourly 1,607 Ccnernt O i f i c ~ 2,023 Proksslonalfloohnfcn1 850 Supervisory 508 Office Exempt 99 1125 1767 769 490 103 , P,ayroll ' - - - Total Net Change -482 -256 81 18 + 4 -- -833 Of the Miahoud and MTF tutrrt of 4284 sa of June 27, 1968, 3394 employees were new hires anel 860 were transfers from other Boeing locations. TRAINING Paid-time training increased during F Y 1968 with 14,677 employees completing 1474 classes. In FY 1967, 8182 completed paid-time training classes. Of the 14,677 employees who received paid-time training during FY 1968, 1641 completed 296 certification classes ; 1808 completed 5 12 re-certification classes; and 11,228 completed 666 systems, skills and management courses. MTF training requirements have been supported on a continuing basis. Major emphasis has been placed on certification, re-certification, reliability, and safety training programs in support of critical operations for S-IC stage testing. A steadily declining work force caused a r ~ d u c t i o nin the number of employees particiwatim i n off-hour training programs. During FY 1968, 640 employees cornpleted 55 courses. Durihg FY 1967, 883 employees completed 82 courses. Attendance at seminars, technical sessions, and symposiums ipcreased during FY 1968 with 610 employees i n attendance. During FY 1967 , 341 attended similar sessions. MANAGEMENT DEVELOPMENT PROGRAhn The Management Development Program has been significantly expanded and strengthened during FY 1968. A separate management development function has been established a s a p a r t of the Industrial Relations organization. This function is responsible for the administration of activities leading to early identification, selection, and development of the management talent needed to meet current and future needs. Michoud is represented on the Boeing Launch Systems Branch M magement Development Committee which fe responsible for the formulation of objectives and plans that will ensure effective management development actions. It also identifies improvements, reviews progress, and provides recommendations pertaining to Launch Systems Branch management development activities. Three off-hour management courses were attended by Boeing employees; and 12 paid-time management courses were conducted f o r 680 employees. GRADUATE STUDY PROGRAM As s r e e 9 t of the Boeiarg Graduab Study Broglem, I f amploytsss will receive their Masters degree at the end of the ItSurnmer term in 1968. Additionally, 75 empfoyees took 361 credit hours during the Fall semest e r 1967, and 55 enrolled for 271 credit hours for the Spring semester of 1968. UNDERGRADUATE PROGRAM As a result of the Boeing Undergraduate Study Program that was implemented in FY 1967, four employees will receive their Bachelors degree at the end of the Summer term in 1968. Additionally, 54 employees took 299 credit hours during the Fall semester, 1967 and 37 enrolled for 182 credit hours for the Spring semester of 1968. COOPERATWE WORK-STUDY PROGRAM The Michoud Cooperative Work-Study Program has increased from 28 students in FY 1967 to 50 students in F Y 1968. This represents the largest number of Co-op students of any location o r Division in the Company. Forty-four a r e Engineering students, five a r e Math and Computer Science students, and one is a Management student. PLANS FOR PROGRESS AND EQUAL EMPLOYMENT OPPORTUNW PROGRAMS A special team of investigators from the Contracts Compliance Office of the Department of Defense conducted a formal investigation of the Michoud Assembly Facility in August, 1967. Fourteen recommendations concerning certain personnel practices and procedures resulted from this audit. Subsequent Boeing action taken on each of these recommendations has been acceptable to the Contracts Compliance Office. An Equal Employment Opportunity Administration function was established in October, 1967. This function includes the development, maintenance, and monitoring of affirmative action policies and procedures for all aspects of the Boeing/Michoud Equal Employment Opportunity Program, A Boelng/Michoud Equal Employment Opportunity �Committee was established in January, 1968. I t concerns itself -with all activities related to Equal Employment Opportunity within the Boeingl'Michoud cornplex and assists in the promotion of equal employment opportunity regardless of race, religion, color, sex, age or natio~alorigin. During the reporting period, a member of Boeing Management ww elected Vice-President of the New Orleans Voluntary Equal Employment Opportunity Council. Boeing Hanqement was also represented on bhe boards of the following organizations: (I) New Qrtecule amid Wolfme P l m w C o m a the plmaing a r m of the Unlted Fund: (2) The f2ommuntty Relations Council a biracial group affiliated with State and Nation4 Community Relations Council Organizations; (3) The City Department of Public Welfare; (4) The Citizens Advisory Committee to the Southwest Educational Development Laboratory a committee organized to resolve problems on intercultural education related to Negro and Southern American minorities; 45) The Urban League of New Orleans; (6) New Orleans Area Manpower Advisory Committee a committee that has approval authority for the funding of all training in a seven parish sector falling within the provisions of the Manpower Development Training Act of 1962;and (7) Personnel Advisory Committee of Total Community Action the committee devoted their efforts toward ensuring the success of the Concentrated Employment Program (CEP) - - - - - . All non-supervisory Boeing employees were briefed on the Company's Equal Employment Opportunity policy. Supervisors and prospective candidates for supervision who attended the Introduction to Management course received comprehensive EEO briefings. The Fall and spri$g College Relations Program resulkd in recntiang kamw visiting 21 colleges, seven of which were predominantly Negro. Industrial Relations hosted 30 Job Development Specialists and Center Directors from the 15 Systematic Training and Redevelopment (STAR) Incorporated Basic Education Centers located in Mississippi. A briefing and tour of thenfacilities were included in the visit. Two Negro students from Southern University, Baton Rouge, Louisiana, participated in the 1967 Co-op Program. A former Negro Co-op student of the University of Detroit accepted an offer of permanent employ ment. Seven Negro employees (five supervisors and two nonsupervisors) completed the recently developed Introduction to Management course for supervisors aad prospective candidates for supervision. One of the non-supervisors was later promoted ta supervisory status, D5-12601-5 During this reportirig period, three Negro employees were promoted to supervisory status raising the number of Negro supervisors to six. COMPUTER SCIENCES During FY 1968 the Business Information and Support Services, and Command Media Organizations were transferred from the Information Management Organization to the Program Planning and Reporting Organization. The remaining Information Management Organization was then rede~ignatedComputer Sciences AppUostions (CBA) This wganfz&tion was d@smed necessary to permit CSA to effectively support the conversion to third generation computer systems. During the organizational realignment, a Computer Systems Requirements Organization was created within CSA to act as liaison between using organizations and systems design groups. This organization exercises surveillance over all mechanized data systems from request to implementation, and assures maximum system efficiency and integration. . MECHANIZED DATA SYSTEMS DEVELOPMENT NEW SYSTEMS IMPLEMENTED As-Built Configuration System-The Michoud A s-Built Configuration Management System was successfully implemented with the delivery of the S-IC-4 in March 1968. Many of the reports previously prepared manually for the Acceptance Data Package are now obtained automatically from the mechanized system. The mechanized system examines a specified Engineering design baseline and then expresses the asbuilt configuration of a given S-IC stage as equal to the design baseline, plus or minus some known level of exceptions, Thie provides Boeing Quality and Reliability Assurance with overall configuration management in support of deliveries, as well as data for launch readiness reviews. The as-built system uses the exception principal for recording configuration data. This allows the system to rapidly recognize and/or resolve differences in configuration due to engineering design changes, The system also tracks instrumentation components, traceable parts, time-cycle and age We sensitive parts, retrofit installations, and con£i@ration exceptions. The as-built system: a) Eliminates the need for manual comparisons between two engineering design baselines; b) Provides a concise listing of configuration ex15 �ccptlons in an indcnhred sequence, thereby providing a display of the systems which are in a "no-go" condition due to a configuration deficiency; C) Produces summary- listings and reports on a blnlely basls for Management vfaibility; and g Allows for rapid accountability of as-built conEigwation differences between any two S-IC vehicles. exp'mdcd to serve the needs of MTF and the Boeing Atlantic Test Center (BATC), This will provide a colnmon configuration accountability system for each S-IC from manufacturing through flight. hlTF Recap System-The MTF Recap System, a set of computer programs designed to track Saturn record system papmvark by maintaining a visual listing of open items against stage processing and GSE configuration changes at MTF, has been implemented. This system is directed toward obtaining zero defects testing by providing the necessary visibility for organizing scheclulcd work, tracking open work, and documenting completed work, Operations Change Status Reporting-The Operations Change SL~tusReporting System was implemented during FY 1968. This system's objective i s to schedule and monitor a committed change to the basic contract from the time the change i s committed by the change board to the date of delivery. Reports from this system provide operations management with current detailed status visibility on committed change; a detailed change scheduling tool; and a means to measure performance on committed changes. Some of the other mechanized data systems deveioped during the past year, and a brief description of each, are: Cost Review System-Major modifications were made to the Launch Systems Branch Cost Review System which collects and updates actual labor cost data by task and NASA 533 report line number. These changes increased the capabilities of the system to produce automated graphical displays and management and customer reports of actual and budget data at the task, contract-schedule , organization, and manager levels. CONVERSIOM TO THfRD GENERATION EQUIPMENT We are continuing the conversion of Honeywell computer equipment programs to run on the Univac 1108 computer. The following systems are now being processed on the Univac 1108: Part Requirements, Material Inventory Control, Facilities Equipment A cquisition, Plant Services Maintenance, Southeast Personnel Accounting and Records, Suggestion Records, Filling of Hourly Openings, Stage Cost Control, AsBuilt Configuration, Engineering Release, Traffic Routing, and Facilities Stores Inventory. As part of the conversion redesign, significant compression of programs is being accomplished, leading to reduction in computer run-time and operational set-up time. COMPATIBLE CONVERSION SYSTEM af Equipment and Final Assembly P a r t Shortage System - provides management with better visibility on parts shortages existing in equiprnent and final assembly parts crib areas; b) Packaging Preservation Requirements System a reference file of packing and cratmaintng specifications for all parts shipped from Michoud; and c) Facilities Stores Inventory System maintains inventory control of spare parts and cansumable 16 SfGNlFICANT SYSTEMS MOOlFlCATlONS PERT-VZsuaJ Task Analysis (VISTA), a computer program designed to rtutomatically plot PERT networker on the SC-4020 Digital Plotter, has been implemented. The automation of plotting networks will replace the manual drafting efforts required to update PERTed networks while permitting a one-to-one accuracy correlation of network graphics to PERT tabular reports, The scope of the As-Built System is currently being - supplies stocked for use in the Factory Equipment Maintenance Program, - The requirement that Boeing convert its programming to operate on a Univac 1108 computer with direct access mass storage has led to the concept of a centralized file management system as the most economical and efficient approach to conversicm. The file management system must perform record address lockup, data retrieval, data restructuring, file backup, and access control. Additionally, the system must support operationp under both Univac 1108 Executive Systerns--EXEC 11 and EXEC VEIf. The Compatible Conversion System satisfiee these requirements. A b o , operating as a set of library subroutines available to both Fortran and Cobol worker programs, it supports the following features: D5-12601-5 �utomatic index constructioi~and maintenance for user-specified data files; ata storage, retrieval, and updding commands r direct record access; Automatic record blocking a d deblocklng to increase serial processing speed; d) Standard file backup and recovery procedures; and e) LolSfcd file structuring facilities. The Compatible Conversion System will operate under either Univac EXEC 11 o r EXEC MIZ, allowing conversion of \vorker programs to a stable mass storage interface, The system has been designed and coded and is currently being checked out against both Executives . A l l deliverable data items for S-IC-2 were delivered on or before schedule even though some input data items were received late. The outputs of the system required to support Boeing's presentations to the FLight Evatuation Working Group were available when needed. MECHANIZED DATA PROCESStNG CONVERSION TO UNIWAC 1005 The Univac 1004 Card Processor was upgraded to a Univac 1005 Card Processor, This equipment modification allows usage of internally stored program instructions to execute production processes. Before the equipment was modified, machine instructions had to be wired into a logic panel. This is a timeconsuming process. The programming effort required to put a job into production has been significantly reduced by the equipment modification. OPTICAL SCANNER UTILIZATION NUMERICAL CONTROL A year ago, the use of Numerical Control (NC) machinery at Boeing/Michoud was just beginning. Only the Cincinnati ATC-430 machine was in production. No software was available for this machine; hence, all part programming was manual, difficult, and tedious. Since that time the N/C computing group has modified, implemented, and checked out software (postprocessors) for six N/C machine tools. They a r e the Cincinnati ATC430, Sunstrand N/C-3 Milling Machine, Gorton 2-30 Tape Master, Sunstrand OM-3 Machining Center, Kearney and Trecker Skin Milling Machine, and Cincinnati Veroi-Power N/C Bed Mill. The first three machines are in production status. The other three are scheduled to go in production by the summer of 1968. A l l software packages have been checked out and a r e awaiting machine activation. FLIGHT DATA EVALUATION A system of computer programs developed during 1967 and 1968 to support S-IC flight evaluation was rtsed to process data from S-IC-1 and -2 flights. Some of the outputs of this system, e. g. , tapes confaining re-formatted, calibrated data, are contractually required deliverable data, with a very rigid schedule. Half of the data items for S-IC-1 were delivered on schedule and half were behind schedule for various reasons, includiug late receipt of input da@, unexpected data anomalies, aad processing problems, Usage of the Control Data Corporation 915 Optical Scanner has been significantly increased during FY 1968. Current output volume of cards is approximately 25,000 per month. Applications under development are expected to boost this figure to 100,000 records per month by mid-year. MECHANIZED DATA SYSTEMS STANDARDS Technical standards to direct and control the development and implementation of automated systems have been written and released. Documentation standards for defining automated system requirements, system' design, and maintaining computer program system configuration control are now in force. Documentation standards governing the acceptance test, the user's guide, and the program maintenance guide will be released in the near future. In addition, approximately 120 technical standards have been issued to CSA programming personnel describing the equipment available for use in automated systems ( both second generation and third generation), characteristics of the software on these systems, and guides to efficient use of this computer hardware/software. During the next year it is expected that the initial development of technical standards will be completed. These standards will cover all areas of technical information needed to interface with the Slidell Computer Operations Office contractor, guides to good programWag practice, docwnenWon standards, design stan- �dnrds, nnd progrnn~minglanguage and equipment s b n cf:wds. These standards a r c e.upccterf to contribute to in~provoiidesign of computer programs and to their usc~iiifnessto others by virtue of program generality nrtd comprehensive program documentation. BUSINESS INFORMATION SERVICES During FY 1968 the n u m b r of listings in the Michmd telephone directory and the number of volumes ~ u b lishcd were reduced. On March 20th, the alphabetical section for Boeing was reduced from 5300 name listings to 1735, The number of pages for the Boeing section was reduced from 67 pages to a t o t d of 22 pages. The total number of directories received from the Support Contractor was reduced from 5000 books p e r quarter to 3000 copies. This resulted i n an estimated cost savings of $16,840 per year. On March 14, 1968, NASA restored indicia mail privilegcs to Bocing official mail destined for Washington, D.C ,, Huntsville, Alabama, and Cape Kennedy, Florida. This privilege will result in estimated postage savings to the government of approximately $24,000 per year. During FY 1968 a Michoud directive was revised and published to establish telephone standards patterned after the Boeing Aerospace Group Administrative Services Business Manual. As a result, since October 31, 1967, Michoud telephone equipment costs have been reduced by $2563 p e r month, This reduction represents $30,756 per year savings to the Government. RECORDS MANAGEMENT During FY 1968, approximately 2500 cubic feet of records were received from Michoud organizations and stored in the records storage center. Based on Boeing Aerospace Group records and release cost standards, a savings of $2.65 per cubic foot of records is realized when records a r e placed in inactive status in storage a r e a s as opposed to office areas. I n FY 1968, using this standard, a net savings i n the amount of $6651.50 was realized. A mechanized system, which provides a listing of organization working files, ha^ been developed, TMs system provides a master listing of records, with common Michoud categories and subcategories, including specific types of records, file location, and responsible supervisors. The purpose of the system is to provide rapid identification, location, and retrieval of records associated with cost, schedule, and product technical performance. a The Classified Control Station has comr~letedanother full year of service to the various Michoud organizations without a single security violation. COMMAND MEDIA The Boeing Launch Systems ~oeing/MichoudCommand Media System formally establishes and documents management policies and controls, authority delegations, and practices. During FY 1968, the command media documentation of systems and product control was revised to ensure meeting NASA and Boeing goals. The record system for the S-IC stage was more clearly established with the issue of eighteen new and revised procedures. A new system has been devised to ensure timely response, traceability, and economy for contractual data delivery requiremen& and i s proposed for implementation through appropriate command media. The documentation of the Saturn V interschedule working relationships between Schedules 1, 11, and IZT to command media is now in progress. Management Directives and Operating Procedures a r e forwarded to NASA, on a quarterly basis, as contractual data delivery requirements. * I DOCUMENT CONTROL The Boeing Launch Systems Branch Document Control System, since its implementation, has proven to be one of the most cost effective operations at Michoud. During this reporting period, additional significant reportable savings have been generated and validated through the cost improvement system. Identified savings, associated with the cancellation of documents during preparation (that were considered valid by both Boeing and NASA/MSFC) , were undetermined by NASA Headquarters at the close of FY 1967. ~ k ; e validity of these savings was established during FY 1968 when $480,590 in savings for these activities were approved for the Launch Systems Branch. The total validated contribution of the Document Control System t o the Cost Improvement program through CY 1967 exceeded $13 million, which was 13.57 percent of Michoud and 9.64 percent of the total Boeing Launch Systsrns Branch savings. C - �Document Control participated in NASA/Boeing tiations for the revision of contract deliverable requirements directed toward consolidating Con NAS8-5608, Schedules I and LA, Data Requireme Lists (DRLJ, developed a data management statement sf work, and clearly Identified, through line itsme In the DRL , total data delivery requirement for both contract schedules. Text proposed by Document Control to improve contract h a t a ~ & j g e ment was successfully negotiated into the statement of work. The consolidated DRL and statemen%of work were implemented try Contract DOCUmsnt TNdeS-IC-67-10, S-IC P r a g r a n Deliverable Data, in January 1968. T o fulfill h need to improve contract data delivery management, Document Control participated with Michoud Contracts in developing a new system for the production release, accountability, and delivery of data. The new system eliminates multiple channels for delivering data to NASA and replaces them with a more orderly and cost-effective flow through existing centralized release services. I t also establishes a data serial numbering system, consistent with contract requirements, which permits management accountability and traceability of deliverable data. In March 1968, Document Control issued instructions that changed the focal point for issuing Boeing document serial numbers and implemented a new format f o r requesting document development authorization. These changes simplified the maintenance of the "LSB Document Control Report" by eliminating previously required monthly organizational data inputs. Consolidation of the document number issuance with the preparation of data inputs into one functional area under Document Control has reduced workloads of all organizations. It has also ensured the timeliness and accuracy of document indices. A review of document activity during the reporting period (see Figure 1-41 indicates an increase in the number of active documents during the last year, A substantial portion of this increase is the result of incorporating into the system, documentation that was not formerly included, and for which accountability OX distribution control did not exist. FORMS MANAGEMENT During FY 1968, the LSB Business Forms Management System has continued to be a cost effective aperation. Under this system there has been no out-of- D5-1260 1-5 tock situation in Forms Store during the past year. so, by careful inventory, issue and reorder control, production requirements imposed on the support services contractor for business forms has been decreased by 40 percent while the number of controlled form items has increased 35 percent over the pre- GOVERNMENT FURNISHED SUPPORT SERVICES A t the request of NASA, Boeing conducted a study of its support services requirements to seduce the overall support effort by 25 percent, The FY 1968 neaotiated budget for government furnished support s e k i c e s (less Computer Services) for Boeing/Michoud was $6,973,000 compared to $8,350,000 for FY 1967. The reduction in projected support services was about 16 percent. Actual expenditures, if extended through June 1968 at the present rate, will amount t o $6,458, 600, an additional support services reduction of about 7.3 percent. Therefore, the government furnished support services required during FY 1968 were decreased by 23 percent, or $1,891,000 from the FY 1967 level. As a result of improved communications and coordination between Boeing Reproduction and the support services contractor's reproduction representatives, more Boeing reproduction requirements a r e being accomplished in a timely manner by the support services contractor. This has enabled us to reduce headcount in the Boeing reproduction shop by approximately 30 percent. MICHOUD ORGANIZATIONS REALIGNMENTS During FY 1968, several significant changes were made in the Boeing/Michoud organization structure. T o provide a consolidation of related functions and posture during the first quarter, the Information Management organization concentrated its resources on the task of implementing the new computing equipment a t the Slidell Computer Center. Business information and support services and the command media functions were transferred from Information Management to the Program Planning and Reporting organization. In the second quarter, the Michoud Information hlaaagemer;lt organization was redesignated Michoud Computer Sciences Applicatic~ns, which 19 �ACTIVE DOCUMENTS - CANCELLED DOCUMENTS (RELEASED) III I ChNCELLED WCUMENTS (UNRELEASED) rflflfl/#m t Figure 1-4 Document Activity During W 1968 properly denotes the functional description of the organization. * At the beginning of the third quarter, the S-IC Program test function emphasis shifted from static firing to flight, thus the test evaluation function was transferred from the Systems T e s t organization to the Engineering organization. This change enables the test evaluation involvement in flight evaluation tasks t o be accomplished more efficiently. - I he S -IC Operations organization was realigned in the third quarter of the reporting period. This realignment involved combining all Industrial Engineering organization t o more effectively utilize skills while maintainlag proper support to the manufachtring organization; and consolidating all manu- facturing activities and manufacturing support activities to effectively reduce operating costs without impacting performance schedules. The S-IC Systems Test Manager's office was relocated from Michoud to MTF in the third quarter of the fiscal year to enable Boeing to establish a closer working relationship with the NASA Manager at MTF . The Management Development Coordinator position was established during the fourth quarter of the fiscal year, reporting to the Michoud Industrial Relations Manager, because of increased emphasis on management development and because of recommendations s e t forth in the Launch Systems Branch Management Development Plan. �CONTRACT END ITEMS & SERVICES �SUMMARY Launch of the AS-501 and -502 took place at the Kennedy Space Flight Center (KSC) during F Y 1968. These vehicles were thrust into flight by the S-IC-1 and -2, Both stages, and their Boeing supplied ground support equipment, functioned satisfactorily and no anomalies o r objective discrepancies occurred which adversely affected their flight. The flxrst ~wina;Michoudmadachrred flight stage, the 8 4 C - 3 , ww rhfpped to x l C on December 23, 196'1. This stage is now a t KSC where it is being modified in preparation for the first Manned Apollo Saturn Launch. Several significant incentive milestones were achieved during F Y 1968. The S-IC-4 was delivered to NASA, on-dock Michoud, on August 28, 1967. This stage has remained at Michoud since formal delivery, and la presently undergoing modifications which were originally scheduled for completion at KSC. Also during FY 1968 the S-IC-5 was auccessNly static fired, and S-IC-6 and -7 completed post-manufacturing checkout. At the end of the reporting period the S-IC-8 and -9 had been completely assembled and were in storage a w a i w start of post-mmufaoturing checkout. Also, the SIC-10 was in horizontal assembly, and S-IC-11 through -15 major struckues assembly was proceeding as achecialed. Throughout the fiscal year S 4 C stage and W E d e s m activities were directed toward increasing the quality of the product and resolving problems and anomalies identified. These efforts were supported by various testing programs including reliability, qudification, development, and failure analysis. During FY 1968 Engineering laboratories completed 331 tests. A s a result of the POGO phenomenon experienced during the AS-502 flight Boeing has formed a task force to cope specifically with this problem to assure its slbviation prior to the next 8-IC flight. Quality and product assurance activities were conducted on a continuing basis during FY 1968. The objective of these activities is assurance of the quality of the end item and its components, and assurance that activities critical to missions or programs are ... identified, planned, and accomplished. During the reporting period 55 quality audits were conducted as a part of the quality program. These audits resulted in the definition of 467 discrepancies which have been resolved or are being resolved at this time. The Quality Maintenance Programwas initiated by Boeing during FY 1967 and expanded by Change Orders MICH-544 and MICH-723 during FY 1968. The purpose of this program is to assure the quality of vendor hardware, with primary emphasis on that hardware where failure could cause loss of stage or crew. his program includes Boeing Management visits to vendors, audits of engineering documentation, quality analysis of vendor hardware, and other testing and moffvational techniques designed to improve the quality of vendor hardware. -t DS-12601-5 23 �DELIVERABLE HARDWARE STAGES * NASA/MSFC ASSE t of FY 1968, both the S-IC-1 and -2 e r e they were undergoing prepamtion These vehicles were lwnched, a s part 68, respectively. (Figure 2-1 crh ng mwed from the KSC VAB , Fi S-501 launch. Subsequent to the AS-501 and -502 launches, all available S-IC-1 and -2 performance data, including engiring sequential film and S-IC/S-11 stage separation from the 8-11 stage was evaluated by the Boeing ormance Analysis team. he SdC-1 and Boeing supplied GSE performed ati isaetorfly during AS-501 countdown and flight and, in 1 S-IC-1 mission objectives were met. e of all systems was satisfactory, and ies o r objective descrepancies which urred did not adversely affect overall stage systems performance. mance of all S-IC-2 systems was satisfactory countdown and launch of the iiS-502. Performance of the Boeing supplied S-IC GSE was also satisfactory, and no f d u r e s of components o r systems occurred during launch countdown. No failures o r deviations which occurred in S-IC systems during the AS-502 launch adversely affected overall stage systems performance. The occurrence of the POGO phenomenon (see page 371 caused no problems on the S-IC-2. Specific problems encountered during the AS-501 and -502 launches, and the corrective actions taken to rectify these problems, are discussed throughout Section Kt of this report. Detailed information on S-IC-1 and -2 performance during these flights can be obtained from Documents T5-7000-1, S-IC-1 Flight Report, released January 11, 1968 and T5-7000-2, S-IC-2 Flight Report, released June 28, 1968. S-IC STAGES - BOEiNG ASSEMBLED The S-IC-D was stored in the S-IC booster storage building at MTF at the start of the fiscal year. On November 10, 1967, it was erected in the S-IC static stand a t MTF for a s e r i e s of fuel tank drain tests, h commenced on December 18, 1967, and were leted on January 17, 1968. (See anti-vortex tests, 75.) On February 1the stage was removed the test stand and on February 6 was again placed rage in the booster storage building at MTF. 1968, the S-IC -D was placed aboard ansferred to Michoud. It was then n April 23, 1968, where MSFC plans lay a t &e Space Orientation Cen- 1968, the 5-1C-F , in storage at 25 �Michoud, ivils hcing used for crew training in preparation for the S-IC-3 helium bottle changeouts authorized by ECP 0215. The atage rcrnaincd in storage until March 8 , 1968, when it was ~novedto the Michoud Vertical rlssembly Building (VAB) where it was erected on hf~trc-h12, 1968. t2'hiie in the VAB, the duminum forward hnncff i&ring was removed , nnd n steel handling ring was installed in its place. The stage wits returned to storage on hIwch 18, 1968, where i t remained until hlay 20, 1968, when it was moved to the factory for rcmavai of a LOX suction duct required to support the Michoud LOX Suction Duct Flow test fixture whicl~ has been constructed at Michoud to test dynamic chnracteristics of suction lines for the proposed POGO suppression system (see POG0,page 37). Figure 2-3 shows thc LOX duct being removed, Figure 2-4 shows i t installed in the test fixture. At the end of the report period, the S-EC-F was still in the Michoud factory building. where it was erected in the VAB on December 30,1967. Following launch of the AS-502, it was decided that the AS-503 would be a manned launch, For this reason the vehicle was de-erected, and the S-IT stage was shipped back to MTF for a second static firing. A t present, the S-KC-S ia undergoing extensive modification at KSC , with a tentative lamch date in November 1968. Figure 2-4 The S-iC-3 was accepted by NASA (Michoud on-dock incentive milestone) on March 15, 1967. The stage was then placed in storage a t Michoud where it was located at the s t a r t of the reporting period. During the first half of FY 1968, eighty-one modifications were incorporated into the S-IC-3 at Michoud. Formal retesting of the S-IC-3 prior to shipment to KSC began on November 13, 1967. Retesting was completed on December 5,and the S-IC-3 was accepted by NASA on December 11, 1967. The stage was then placed on a barge on December 21, departed Michoud on December 23, and arrived at KSC on December 27 26 LOX Duct installed in POGO Test Fixture The S-IC-4 was undergoing refurbishment and poststatic checkout at the start of the reporting period. Post-static checkout was completed with customer acceptance of the simulated flight test on August 16, 1967. The stage was then placed in storage on August 22, 1967. It was accepted by NASA, on-dock Michoud on August 28, 1967 (3494.6 out of a possible 3498.6 incentive points were earned) and it remained in storage until December 27, 1967, when i t was moved t o the stage test facility for modification and retest. Retest was accepted by NASA on March 22, 1968, however shipment of the stage to KSC was deferred by NASA direction. On April 1, 1968, incorporation of all changes that could be "rolled bacK' from KSC began at Mich- D5- 12601~5 �wid. &%adification is continuing, with shipment of the stage to KSC presently scheduled for August 23, 1968. S-IC-5 The s b g e had just been loaded into the static test stand a t MTF at the hsegfnning of FY 1068. Pre-static firing checkout sf the stage was completed, and on August 25, it was successfuly static fired for 125 seconds. Incentive points of 260.0 out of a possible 260.0 were earnod for this firing. (For a detailed descripUon of S-IC-5 static firing activities s e e page 73.) The stage was removed from the static test stand on September 11, shipped back to Michoud on September 12, and moved (Figure 2-5 shows an S-IC stage being moved from the Michoud factory building) into the stage test facility f o r refurbishment and modification on November 15, 1967, Refurbishment and modification were discontinued for a period of time but were renewed on January 30, 1968. On April 1, 1968, the stage began preparation for post-static checkout, scheduled a t that h e to commence on April 22, 1968, Post-static checkout was deferred at NASA's request and, at the clwe of the reporting period, is scheduled tcJ commence on July 8, 1968. !f------ -- . . Systems 'tA" instrumentation (hardwire instrumentation for static firing purposes only), and incorporation of committed modifications, It was shipped to MTF on March 1, 1968 and erected in the test stand on M,wch 4, 1968. Stage power-on wns accomplished on April 4, but on April 23, a t the direction of the Program Executive, S-IC-6 acceptance tests were suspended s o that proposed POCO suppression modifications, resulting from AS-502 flight analysis, could be studied for possible incorporation and testing on the S-IC-6 prior to the decision to incorporate them on the S-XC-8, A raview of changes affecting the stage was then conducted to decide which changes would be practicable for accomplishment prior to a later static firing schedule. At the end of the reporting period, S-IC-6 static firing was scheduled for eary August 1968. S-IC-7 Post-manufacturing checkout of the S-IC-7 began on August 14, 1967 This activity was completed on November 13. Maximum incentive points were earned for achievement of this milestone, but they a r e being held in abeyance pending negotiation of SA MICH -662 (see page 3). The stage was placed in storage on November 22, 1967. " _*-""f Figure 2-6 shows the S-IC-7 in storage in the Michoud factory building. On March 13, 1968, the S-IC-7 began installation of Systems "A" instrumentation (hardwire instrumentation for static firing purposes only) and incorporation of committed modifications. At the close of FY 1968, the stage was scheduled to be delivered toMTF (to begin preparation for static firing) onSeptember 13, 1968. . S-IC-6 The S-IC-6 was undergoing post-manufacturing checkout at the end of FY 1967, Post-manufacturing checkout was completed on July 24, 1967, with customer acceptance of the simulated static firing test. (Maximum incentive points of 299.6 were earned for attainment of this milestone. ) The stage remained ak. Michoud through February 1968 for storage, inst&&%ionof Figure 2-6 S-IC-7 Stored in Factory Building �S-IC-8 Vcrtlcnl nssembly of the S-rC-8 was completed Septcmbcr $1, 1967 imnc? hoz.izontni assembly begon the following clay. (Figure 2-7 shows the S-IC-8 invertical assembly and F i w c 2-8 shows ft being removed from the vcll.tict11 position in the RIichoud V A B , ) Due to modifications to thc ~vorkingschedule, the vehicle remained in a fitctory work position for horizontal assembly and morlificaliw incorporntion until May 110, 1968, when it was tmnsfcrred to a factory storage position where i t will remain for an indE.finite period. Several proposals have been made during the past year to initiate a factory verification test with the S-IC-8 vehicle. This test would consist primarily of a proof pressure test Eo check for leakage in the LOX and fuel tank systems, At one time, in mid-March 1968, dl preparations were completed and readiness reviews were held with the Mickoud Operations Manager, but performance of the test in the factory was suspended a t the last moment by NASA directive. S-iC-9 All major structure@for the vehicle were completed furing FY 1968. Vertical assembly was completed February 22, 1968, and horizontal assembly began the following day. Horizontal assembly was completed June 17, 1968, and the vehicle began a period of modification incorporation. Figure 2-9 shows F-1 engine installation in an S-IC stage during horizontal assembly, Delivery to the Michoud Systems Test organization for post-manufacturing checkout is presently scheduled for November 14, 1968, Figure 2-7 S-It-8 i n Vertical Assembly Figure 2-9 Figore 2-8 28 S-IC-8 Being Removed From VAB F-1 Engine installation in S-IC A l l major structures for the S-IC-10 were completed during the past year. Figure 2-10 shows completed S-IC propellant tank being moved from the Michoud factory building. Vertical assembly of the stage was completed June 18, 1968, and horizontal assembly began the following day. Delivery to Systems Test for post-manufacturing checkout is presently scheduled f o r Junuary 22, 1969. D5-1260 1-5 �?, * -".***--- -)r*$, m--~-7*.-.e.*Cw-"w-*;P"Q.~*1 - ' r* --' rr*.llla"W? t I I included one refurbishment unit for RP&VE and two KSC generd units. ? 9 i 1. f 1 .* . --- Figure 2-16 ---__-- -. --- '$ \ 11Y--- S-iC Propellant Tank Being Moved From Foctory During the past year, CCP 9289 (launch support hardware at KSC) , which established Michoud as the focal point for umbilical refurbishment, was initiated. Under this concept, all five of the S-XC umbilical carriers installed on a LWT will be removed from that LUT after a launch and returned to Michoud for refurbishment and updating. The present contract provides that a s e t of umbilicals be supplied for launches through the S-IC-15 with replacement of the units on each LUT after the last presently scheduled launch. Assembly i s now in progress on sets for the S-IC-4 and -6 and production support. *.I - .Jd S-JC-IITHROUGH -15 Assembly was started on the 3-XC-11 through S-IC-14 vehicles during the past year. Several of the major structures for the S-IC-11 have been completed. Assembly is proceeding as scheduled on the S-IC-11 through -15. Figure 2-11 gives the percentages of completion on S-IC-11 through -15 major structures a t the end of the report period. The remaining three units of Modification 122/174 pneumatic equipment were deivered to KSC during the past fiscal year. The helium and nitrogen sections of the LUT #3 pneumatic console were returned to Michoud Operations by Engineering Laboratories in mid-August 1967 following completion of a life-cycle test, Refurbishment and updating of the two units was accomplished on an accelerated basis, and the last of the two units was delivered to KSC on January 5, 1968. The third unit, the LUT Number 3 pneumatic checkout rack Number 2, was delivered to KSC on January 17, 1968. S-IC STAGE SUPPORT EQUIPMENT Figure 2-1 1 Percentage Complete June 27, 1968 - S-IC stage transportators Due to the revisions to the vehicle delivery schedule during the past year, S-IC stage transporters have become the pacing item in the completion of vertical assembly at Michoud. This is due primarily to the length of time the transporters a r e required to stay at KSC , and the number of vehicles in process at MAF in the horizontal position. At present, plans axe being made to work around the transporter shortage problem by placing vehicles in horizontal assembly on storage stands. T o provide a more definite resolution to this problem, action will also be taken in the near future to attempt to have transporters released from KSC as soon a s a vehicle is erected. b) S-IC forward handling rings The provisioning of handling rings to support the lift and join of the forward skirt has become an a r e a of concern during the past year. Because the S-IC-3 handling ring could not be released in time to support the S-TC -10, it became necessary to erect the S-IC-F vehicle in the VAB and change - Major Structures GROUND SUPPORT EQUIPMENT KSC EQUIPMENT Thirteen end items required by MICH 112, CCP 9001, were delivered during the past fiscal year. Fifteen end items remain to be delivered. T h e last three units of Modification 123/185 umbilicals were delivered in the past fiscal year. These units D5-12601-5 - a) - 29 �out i t s aluminum handling ring for anPIISFC supplied steel handling ring. Yet even with this measure, it was necessary to waiver postproof-load test impectionin order to lift the forward s k i r t on schedule, The 5-16-3 h,wdlng ring i s now programmed for turnar*aund utfllzntian on tho S-IC-11 vehicIpt, and again does not support the MAF demand date, El oivever , efforts a r c now being made to accelcr:dc releaso of this handling ring from KSC , and with the use af premium time effort during rccyclo teat, the problem may be resolved. DESIGN AND ENGINEERING S-IC ENGINEERING DOCUMENTATION other committed changes. There were 3679 documentation packages released, of which 1961 were retrofits. Documentation releases associated with change action consisted of the completion of documentation for 117 chmgus ars listed in Appendix A, Changes initiated included 185 ECPs, 25 PRRs and 8 CCPs for a total of 218 changes a s listed in Appendix 3. During F Y 1968, Boeing Engineering worked ~ l o s e l y with the Computer &fences Applications organbatian ta assure that the Automtitic Rdeass &atem conversion from Honeywell to Univac computing equipment was successful. As a result, a high level of confidence can now be placed in the Automatic Release System, and the quality and timeliness of the required reports are excellent. S-IC STAGE WEIGHT STATUS Engineering dncumentatfon releases for F Y 1968were of a sustaining nrtture and consisted of retrofit and The final S-IC-1 stage dry weight a s determined by �the weight and balance log was 307,550 pounds pounds over the Contract End Item (CEI) speci tion weight of 305,284 pounds. The final S-ICdry weight a s determined by the weight and bal log was 306,159 pounds. This final weight is 137 pounds under the CEI specification weight of 306,2 pamde, T h s calculated dry w i g h t of the S-IC-3 stage for which Boeing has responsibility has increased 353 pounds during this reporting period. The F-1 engine weight did not change. At this ti Bocing is 669 pounds under the specification wei for 5-16-3. Variations in S-IC-3 versus S-f weight are plo-d Q Figure 2-12, Those do not include R&D fnstswnentauon, which with each vehicle (S-IC-2 through S-IC-5). Figure 2-13 represents the CEI spectfication wei CEI specification weight (less engines), 330 rent weight (R&D less engines), current dry (less R&D), and dry stage weight {R&D) for S-IC-2 through -15, A comparison of current we versus CEI specification weight for the S-IC-3 is included. - - S-IC STAGE DESIGN SERVOACTUATORS - Hydraulic Research servoactuator spring failure During pre-static firing checkout of the S-IC-5 a t NTF, the locks-off null position test revealed that the Hydraulic Research (HR) servoactuators on engine number four were not within specified limits, thereby causing erratic response. The cause of this out-ofnull positioning was traced to broken torsional springs that a r e designed to. preload the rotational mechanical feedback mechanism in one direction to remove backlash in this portion of the actuator control loop. Investigation revealed that the spring failure was due to contamination during heat treatment, As a result, HR servoactuators on the S-IC-1 were replaced with Moog servoactuators, and we were directed by NASA to replace the material used in Ihe failed spring (17-7PH steel) with a material not susceptible to s t r e s s corrosion. The actuators removed from S-IG-1 were used on the S-IC-2 after incorporation of improved process 17-7 PH steel springs, and Inconel 718 was selected a s the new material for the S-IC-3 and subsequent stages. Servoactuator s t r e s s corrosion- Failure of a Moog 50M (MSFC prmured) servoactuator occurred during bench test* at MSFC in February 1968, Severd other failures were subeequeatly dfseovered on D5-12601-5 tor bodies at both Moog and MSFC, MetalluranaIysis of the f i r s t f a i l u ~ eindicated that s t r e s s osion cracking occurred at the parting plane of e forged body, which m e constructed of 7075-T6 uminum. ~ e c a u s ethe S-1C-2 had four actuators this model installed, a change was initiated to reme them with BOB (Boeing procured) servoactuars. Boeing procured servoactuators were acceptable because additional processing controls, to minimize residual tension stresses on the surfaces f the actuator bodies, had been imposed during abrication, As a result of the above events, both Moog axl Hydraulic Researoh (Wlt) servollnkratDrs a r e being redesigned, and a test program for comparing s t r e s s corrosion resistance of 60B and 50M actuators has been initiated. 7075-T73 aluminum will be used a s body material for both the Moog and HR servoactuators, The Moog cylinder will remain 4340 steel while the HR cylinder will be changed to 7075-T13 aluminum. Miscellaneous other components win require processing modification to preclude s t r e s s corrosion. Test evaluation procedures for comparing 60B and 50M servoactuators will include accelerated s t r e s s corrosion testing bv alternate immersion in 3.5 percent salt water and X-ray diffraction measurements to determine residual s t r e s s levels on actuator body surfaces. Completion of the actuator redesign program is scheduled to provide production parts for use on the S-IC-6. The 6 0 3 (Boeing procured) 50M (MSFC procured) comparison study is scheduled for completion in September 1968. - Servoactuator redesign to eliminate s t r e s s corrosion and hydrogen embrittlement - Change Order MICH 738 directed Boeing to redesign servoactuators to eliminate all s t r e s s corrosion and hydrogen embrittlement susceptible materials, A review of all materials used in servoactuators has been conducted and material changes will be accomplished. Servoactuator electrical filter design-During S-IC-1 static firing, unexplained electrical noise in the Moog servoactuators input signal, accompanied by random movement of the actuator, was experienced, fnvestigation revealed that the observed noise resulted from vibration of the servoactuator torque motor that occurred in sufficient magnitude to saturate the flight amplsier and cause loss of actuator control. A change was initiated to reduce the noise level of Moog servoactuators on S-IC-3 through -10 by the use of a filter assembly that has been successfully tested in actual firings on the single-engine stand a t MSFC during &ne 1967, On August 31, 1967, S-IC-5, the f i r s t stage equipped with the flight configuration 31 �i- CEI SPEC. WEIGHT S- l C-2 - BOElNG CURRENT WEIGHT (R&D) (LESS ENGINES) (LESS ENGINES) ~ E SPEC. I WT. 306,296 " AS REPORTED BY THE F l N A l WEtGHT AND BALANCE LOG. . S-I C-3 WEIGHT STATUS 12-30-67 6-27-68 CHANGE 305,435 211,976 305,788 212,329 4.353 +353 7,931 7,931 0 304,681 305,498 +817 212,181 7,847 212,998 7,847 t817 0 I, CURRENT WEIGHT A. DRY STAGE (INC. R&D) B, DRY STAGE (INC. R&D) (LESS ROCKETDYNE) C. RESEARCH AND DEVELOPMENT ilR&D) II.CEI SPECIFICATION WEIGHT A. CEI SPEC. WElGHT (INC. R&D) B. BOEINC PORTION, CEI SPEC. WEIGHT f INC. R&D1 C. R&D, CEI SPEC. WEIGHT RESEARCH AND DEVELOPMENT INSTRUMENTATION (R&DI (CURRENT) S- 1 C-2 S- IC-3 S- IC-4 S-1C-5 7,950 7,931 5,407 5,177 POUNDS POUNDS POUNDS POUNDS C Figure 2-13 32 Breakdown of S4C Stag6 Weights D5-12601-5 �filter msembly, was static fircd at MTF, and malysis of thrust vector control data showed that actuator8 equipped with the filter asr;embly performed within end item test plan requirements, ELEMRICAL 01STRIBUTORS During FY 1968 the Electrical Distributor Qualification Test Report was revised to incorporate certain exaggerated environmental test results and minor changes requested by MSFC , including changes to determine the effect of foam fn electrical distributors. Testa were conducted on cr distributor without foam, and results indicated that foam did not affect component o r structural dynamic responses. To eliminate concern with foam expansion, deletion of BMS 8-38 Sta-foam from electrical distributors wm proposed, However, this modification was disapproved by NASA. Inspection of printed circuit boards in electrical distributors revealed that some solder joints were cracked. Analysis indicated that the cracked solder joints were caused by differential rates of thermal expansion between component leads and board material, Environmental tests, thermal shock, and vibration verified the functional integrity of printed circuit boards with cracked solder joints. To eliminate cracked solder joints, manufacturing processes were revised to reduce stress in solder joints, and redesign of printed circuit board was initiated to provide strain relief for susceptible solder joints. An electrical distributor redesign study was initiated dufing the reporting period. This study will define distributor design criteria and investigate application of advanced packaging, interconnection, and termination techniques to electrical distributors. The study goal is to determine methods of improving distributor maintainability. During rework of S-IC-3 spare distributors to S-IC-1 stage configuration, misaligned and protruding contact members were noted in methode printed circuit card connectors. Subsequent discrepancy inspections revealed that these conditions were prevalent in a large percentage of installed connectors and in new connectors in stores. Cracked contacts were also noted in a number of connectors during these inspections Investigation revealed that the conditions were not design discrepancies, but resulted from inadequate control of materials and dimensions, which is inherent with parts procwred to vendor part n m bers with no control by the procuring activity, To provide tighter c&ols atld to assure producti~nof eatiafa&ry parts, a cormecEor specification was . 335-12801-5 originated, and a change was initiated to replace the FD744-%-SF connectors with MBC455 connectors on S-IC-3 and subsequent stages. Since no failures of the FD744-%-SF connectors had occurred during qualification, reliability, development, subsystem or stage level tests, or during numerous static firings, they were retafned on S-Ie -1 and -2, Figure 2-14 illustrates the S-LC power distribution system, Figure 2-14 S-IC Power Distribution System LOX FllL AND DRAIN VALVES During countdown demonstration testing of the AS501, LOX fill and drain valves were found to be leaking. Analysis of the valve failure revealed a eircumferential crack in the main seal, which is believed to be caused by severe thermal stresses induced in the teflon seal when it contracts, at cryogenic temperatures , at a rate faster than the surrounding metal. These stresses could also be enlarged by tolerance buildups, high flow rates, or valve cycling. This failure could not be duplicated during follow-up testing by the vendor, Parker Aircraft Comp+ny. Boeing assumed the risk of flying the S-IC-1 and -2 without changes to these valves. These decisions were based on the following: a) The valve has been installed in 18 locations per stage on the 8-1 and S-I3 stages with no eimilar failures experienced; b) Only two other failures (one seal cracked and 33 �onc showing cvidcncc of a crack starting) of this type had bccn experienced on the S-IC stage; c) A review of quality records was unable to attributc the failure to any specific lot of seals. Visual examination of approximately eight other, scals , inclucting one from the e.me lot as the S-IC stage valves, revealed no additional cracked seals; ,and d) Analysis indicates a high probability that any leakage would be GQX rather than LOX in the in installed valves. In event of a cracked ~t?d addition, the SA-501 mission revealed only gaseow leakage in the valve area. ORtGlNAL DESIGN S-IC PROPELLANT DISPERSION SYSTEM - Installation interference As a result of the problems encountered during installation of the Flexible Linear Shaped Charge (FLSC) on both the S-IC-1 and -2, the ordnance cowling installation has been redesigned, The redesigned cowling consista of m openfaced box with cover plate, and allows lateral insertion of the ordnance. Rework operations on the S-IC-3 ordnance included cleaning of the existing propellant tank cowling and replacement of the cowling on the forward skirt and intertank with the openface and cover-plate configuration mentioned above, The propellant tank cowling was reworked rather than removed because this cowling is bonded to the REDESIGN 1 :iguse 2-15 LOX Fill and Drain Valve Redesign The vendor has redesigaed the main seal area by splitting the existing one-piece seal into an internal dynamic seal arsd an external static seal (see Figure 2-15), An additional row of circumferential springs on a metal seal back-up contains the internal dynamic seal and provides the sealing surface. The new design has been subjected to limited qualification tests to assure that all design requirements can be met, and the redesigned valves will be incorporated into S-IC-3 and subsequent stages. However, qualification testing revealed that existing test procedures could allow a valve to qualify and yet experience leakage in stage use after repeated dry cycling during stage test and checkout. This condition has been evaluated by Engineering with the conclusion that the condition is an acceptable risk for the S-IC-3 Mght. However, efforts to resolve the problem are continuing and Engineering will initiate changes proposing the development and procurement of an improved design. 34 tanks and rebonding requires environmental control that is not available at KSC On S-IC -4 and on, the existing bonded cowling is being replaced with the new, open-face cowling. . - Support bracket failure During a routine inspection of the S-IC-1 fuel dispersion system installation, it was discovered that 31 support brackets had become unbonded. Investigation concluded that this failure resulted from sustained load application to the support brackets. This situation has been avoided on . subsequent vehicles by assuring a clearance between the cowling and the support strap. The failures on the S-IC-1 were dispositioned by removing the failed brackets and support straps. On the S-IC-2, failed brackets were removed, all support straps inspected, and shims were installed to provide desired clearance, An inspection of the support bracket installation on S-E-3 and -4 reveded only one failed bracket on the D5-12601-5 �EtECTRlCAL INPUT OMMAND DESTRUCT I Figure 2-16 J S-IC Propellant Dispersion System S-IC-3 and none on the S-IC-4. All support strap installations were inspected and reworked as required on all subsequent stages. Figure 2-16 is a schematic of the S-IC' propellant dispersion system. PROCEDURES FOR CHANGE-OUT OF TIMEICYCLE SENSITIVE ELEMENTS LOX ENGINE CUTOFF SENSORS - Solar Cell Redesign The LOX engine cutoff sensor solar cell has been replaced with a solar cell that is reliable at cryogenic temperatures. This action was taken because the previous solar cell had a history of failures. - During FY 1968 a change was initiated to resolve difficulties encountered in controlling time, cycle, or age sensitive S-IC parts, and to implement a new 50 percent life requirement at stage delivery. Life limit requirements, which were originally listed in Document D5-12713, will be released as new Class I documentation. The new Class I documentation will define the life limits and life apportionment by test phase of all S-IC time, cycle or age sensitive.parts. This documentation will also define the disposition of parts a t the end of life limits and, if parts can be reworked, the work necessary to restore the time, cycle, or age life to zero. Center Engine Redundant LOX Cutoff Sensor A new optical LOX engine cutoff sensor was developed, for installation in the center engine LOX duct, to provide a redundant method for initiating center engine shutdown upon LOX depletion (see Figure 2-17). This change is effective on S-IC-2 and S-IC-4 and subsequent stages. This change is not necessary on the S-IC-3 because the center engine on this stage is shut down by a timed signal from the instrument unit. LOX VENT AND RELIEF VALVES A redesign of the position switches on the LOX vent �and relief valves was initiated to resolve the following problems: a) Oil contamination could result in switch failure causing countdown delay due to the LOX vent valve position interlocks; and b) The actuator post-to-spring spotwelded joint failed during the S-IC-2 CDDT , resulting in an electrical short and loss of "open" position indication, which caused CDDT delay. PARKER VALVES STRESS CORROSION To eliminate the possibility of s t r e s s corrosion in the Parker Normally Closed IN.C ) Fill and Drain Valves (LOX and fuel), N. C LOX Interconnect Valves, and Normally Open (N. 0. ) LOX Interconnect Valves, the actuator housings of these valves were reheat treated to a 7075-T7351 condition. This change was initiated on stages S-IC-2 and on because failure of the actuator housings could result in loss of actuator pressure that would cause closing of the N C , valves and opening of the N .O vaIves If this occurred during fuel and/or LOX fill operations, the fuel and/or LOX fill and drain lines could rupture because the GSE would not be able t o shut off the fuel/ LOX supply in time to prevent excessive surge pressures. . . . . . LOX INTERCONNECT VALVE During the reporting period three Whittaker LUX interconnect valve shafts failed, and a fourth was f d to have circumferential cracks, that were 36 identical to those found on the three failed shafts, indicating a potential failure. Of the three valves that failed, two failed during functional testing, and the third failed during reliability test cycling. Seven other valves were disassembled and their shafts were magnetically inspected. Of these seven, one was found to have circumferential cracks on the shaft. To prevent such failures, which would render the valve inoperative, the shaft material was changed (S-IC-2 and on) from 440C to Inconel 718, heat treated to 180,000-200,000 psi. F-1 ENGINE LOX SEAL PURGE REGULATOR The LOX Seal Purge Regulator is a flight critical component that has been subjected to prolonged operating time during prelaunch test activities at KSC Because this additional operating time was not anticipated during initial design and testing, a reliability test program was initiated to simulate five complete life cycles. There were no critical failures on three test regulators each of which waa subjected to a total of 840 hours of operation to satisfy the reliability test that simulated static firing, prelaunch, flight environments, and service times, A burst test will be conducted using one of the reliability test regulators to determine any detrimental effects the reliability Iff@~ y ~ f might b g have h%dBI t h rfa@atorr This @&tier erck@&ledto kgin in Augwt 1988, . RETROROCKETS - During FY 1968 there have been several major D5-1260 1-5 �problems concerning S-IC retrorockets. These problems and their resolution are: - Propellant cracks, voids, and separation Problems of this type have occurred on S-IC retrorockets. ' I o solve such problems as they arise, Z'hiokol Chemical Corporation (the vendor) details propellant problams on Material Review Board (MRB) forms, submits the MRB forms t b Boeing Engineering for approval, and then proceeds to take the approved corrective actio~. Localized thin aroas in rocket cases - During a drwwintJ operation that ww used in ttra rnfu~uf~oftrre of rocket cases, longitudid thin strips, called creases, were generated in the case walls. To resolve the problem, a stress analysis was made on each case-to determine the maximum pressure each would withstand. The three cases with lowest wall thickness in the creases were then hydroburst. These operations indicated that the remaining creased cases were acceptable insofar as design strength requirements are concerned. Overdrilled holes in rocket cases and out-of-round rocket cases These problems were resolved by stress analysis and the test firing of one rocket. The test rocket had an unacceptable out-of-round condition, and the 1/4 28UNF holes in the head end were overdrilled, Thiokol created a "worst possible'' condition in the roeket by extending the already overdrilled holes through the case and into the propellant. The bolts were installed and the rocket was fired resulting in nominal performance parameters and no evidence of case deterioration due to either discrepancy. - seconds to T+135 seconds, a significant longitudinal oscillation of 5 cps built UP and then died out after reaching maximum at T+126 seconds. Acceleration, thrust, and propellant pressures were all in phase, indicating a closed loop instability, called POGO, that limit cycled, Accelerations reached 0.8 gts peak-to-peak at the Command Module interface and 0.4 g's peak-to-peak on the S 4 C stage. These oscillations can affect payload structure and impair the effectiveness of the astronauts, The Crolution t;o this problem involves a change to the LOX delivery system to effect a change in propellmt line freqwncier , t;heeeby dsloclupli~the orsefllatfm and estaXslishing stability. A full-scale analysis is underway to determine and incorporate the solution to this problem prior to the S-IC-3 launch. Several POGO solutions have been considered, and the two prime corrective systems currently being considered are a helium injection sysbm (ECP 0442) and prevalve accumulators with helium injection fECP 0446). A brief description of these systems follows. a) This system involves injection of gaseous helium into the upper portion of the LOX suction ducts through existing bosses of the four outboard engines during the time that POGO could occur. The helium supply will be tapped off the high pressure side of the stage helium manifold, then routed through shutoff valves, regulators, and orifices to manifolds located in the intertank area, and then through check valves into the suction ducts. - S-IC-1 and S-IC-2 flight retrorocket performance exceeded prediction Both the S-IC-1 and S-IC-2 flights have revealed retrorocket motor performance in excess of that predicted. Pressure transducers are used in flight to measure the performance of each of the eight retrorockets. Investigation revealed that Tkiokol uses tubing filled with grease to measure performance while the Boeing instrumentation is coupled directly to the pressure chamber and exposed to direct pressure and temperature transients. Because flight performance was predicted on Thiokol measurements, it was necessary to run comparative instrumentation tests, The results of this testing indicate that flight instrumentation read high in an indication of excessive performance. Final reso* Iution of tNta problem i s not complete for W8 report;fng period, - POGO During the S-IC-2 flight, in the period from T+110 D5-1260 1-5 Helium Injection System (ECP 0442) b) Helium P revalve Accumulator System (ECP 0446) This system involves injection of helium gas into the LOX prevalve cavities, thus enabling the prevalves to serve as accumulators. Onboard helium will be provided by tapping off the high pressure side of the helium manifold. As a result of the POGO resolution effort an extensive testing program has been undertaken by Boeing Schedule I, Numerous component tests, development, reliability, and qu&f1cation, have been initiated to help raaolve thia problem. A LOX suction duct flow test fixture, which is being used to test dynamic characteristics of suction lines as a result of proposed POGO suppression s y s t e m , has also been constmcted at Michoud, 37 �AIR SCOOP BIMINATNIN hfSFC hnx ngrccd to delete the base air scoops for st,ngc,s S-IC-3 and on, This i s being done because nnnlysis intficatcs that the base air scoops used on the S-IC a r e not rrqulrcd to maintain temperatures in tho base rugtan within ncceptztblc levels. The 5IC-1 flight verified this m d y s f s when the data was cx,unined and thc actual base environment was found to be much less scvcre than the design environment. This data indicnted that air scoops were not necessac far coaling, Scoop elimination was also desirnblc Imm thc et.mdpoint of weight (a~>proximably ,500 Ibs,), cost, and possible interference with LUT hardware during llft-off; and a chmgc to provide a rain cover ovcr t h scoops ~ to prevent deflection of rain water on thc fnsulatcd base area surfaces will also be avoided by scoop elimination. Data from the S-IC-2 flight confirmed that the scoops are not required. The base environment on the S-IC-2 was more severe than S-16-1, as expected, but still less than design levels. HEAT SHIELD - Heat shield material The basic ingredient of the &I-3 1 ccramic hsulation originally used on the heat shield was Tipersul. Therefore, upon notice from the I)upont Company that production of Tipersul would be discontinued, Boeing stockpiled a supply to support estimated S-IC requirements. However, due to an unexpected high usage rate in production and refurbishment operations, the stockpile proved insufficient. As a replacement for M;3 I, the MSFC M&P Laboratory developed a new insulation, FTA 442A. The Rohr Corporation performed development tests and fabricated production panels with the new insulation f o r qualification. Tests were run subjecting the panels to the predicted flight environmenb. As a reliability test, panels were subjected to an additional 140 seconds of acoustic test with minor damage, In a separate test, engine shutdown followed by a flight cycle was simulated with favorable results. Based on preliminary data and reports, the new mateda.1 appears more than adequate for flight use, and will be used, rather than Tipersul, for the heat shields on S-IC-I0 through -15. " - Heat shield delamination During the S-IC-1 flight, two thermocouples located on the heat shield a t holddown M i t i o n III indicated a sharp temperature rise a t approximately T+110 seconds. During the S-1C -2 flight, two thermocouples located on the heat shield 38 at holddown Position Il indicated a sharp temperature rise at T+96 seconds. These anomalies were attributed to cracking and/or delamination of the M-31 ceramic insulation. TV camera film at Position I on the S-IC-2 flight showed a triangular area of delamination approximately 10 inches on each side, bat no thermacouples axe installed in this area to record the effects of the delamination. This problem appears to be localized because average coldside and brazeline temperatures were 72OC and 185OC, respectively, These low average temperatures indicate that, even though local damage may have occurred, the heat shield remained effective. Additional vibration and acoustic measurements will be included on the S-IC-3 heat shield to determine the cause of the delamination. FORWARD SKIRT TEMPERATURE Insulation was applied to the S-IC-1 forward skirt to prevent high temperatures. Data received from the S-IC-1 flight indicated that temperatures were lower than anticipated. However, because the insulation thickness was not strictly controlled, this data is not completely reliable. Therefore, controlled thickness insulation will be placed on the S-IC-3 at thermocouples, and temperature data will be gathered during its flight. If this S-IC-3 flight data indicates that insulation is not required, it will be eliminated from S-IC-4 and subsequent stages. STAGE RAINWATER DAMAGE While the S-IC-1 was on the pad at KSC, rainwater entered the thrust structure area through the electrical cabling access opening underneath the electrical tunnel and caused water damage to certain electrical components. To prevent rainwater from entering the stage, a type of adhesive tape was applied to the electrical and pressurization tunnels and other affected areas on S-IC-1 through -3. Because this tape application is a temporary measure, rubber and metal seals will be installed on the S-IC-4 and following stages. FORWARD UMBILICAL DOOR Film taken of the launches of the S-IC -1 and -2 disclosed that the forward umbilical door interfered with the umbilical disconnect cable at liftoff and remained open during flight. Although no apparent stage and only slight umbilical damage resulted, the forward umbilical door was redesigned to prevent interference with the disconnect cable and to ensure proper closure of the door during Right. The change was made for S-IC-3 and on, but the change could not be made to the S-fC-2 due to schedule impact. D5-1260 115 �measurements. Of the 880 active measurements, 865 provided valid data. OESICCANT FILTER UMlTS The desiccant filter unit is comprised of a particulate filter, which is 100 percent efficient in removing particles 50 microns or larger, and a silica jell desiccator which ha$ the capability to reduce the relattve hum?tdiw of Znnawiw air frum 98 percent to 65 percent. NASA has reviewed the application of desiccant filter units to be used on the S-IC propellant tanks and approved their usage during all MAF operations, This change constitutes a major cost reductien because the prc%viowlym a d positive greseurization ayrtrttn required c m a t monitorif af the equipment. The desiccant filter systam requires monitoring only to the extent of changing out the desiccant portion approximately unce each seven to ten days. . The mags of the desiccant alter system on propellant tanks of the S-IC stage in storage was applied earlier, and its usefulness and convenience has been establshed. Recently, relative humidity samplings of the tank interiors were found to be well below a new customer requirement of 40 percent maximum. SLOW RELEASE MECHANISM Boeing Schedule I and II were concerned about the number (12) of slow release mechanisms (SRIVI) and the possibility of inadequate lubrication of the SEW with the KSC procedure of greasing after SRM assembly of the pin in the die. , Three spares S-IC-2 slow release mechanism, lubricated to a new KSC procedure, were pulled in the MAF laboratory. The peak extrusion loads of 66, 63, and 69 kips were in the low portion of the range of peak loads obtained during the developmental test program, Loads analyses, with 12 SRMs having these latest test data characteristics, indicated that although the vehicle responses have increased, in all cases these vehicle responses remained within design limits. Also, the time required for SRM extrusion had dropped indicating less probability of AS-502/LUT interference than would have existed with a 16 SRNl configuration having peak force values of the original specification. Therefore, a properly instrumented 12 SRM configuration using thc4 new KSC SRM lubrication procedure was used on S-IC-2 and will be wed on S-IC-3. 1NSTRUMENTATFON - Flight measurements On the S-IC-1 flight there were 854 active and 18 waived measuremeats. Of the 854 active m e ~ u r e m e n t,s 831 provided valid data. The S-IC-2 flight had 880 active and 13 waived . - Thermocouple bond failure Thermocouples bonded to the LOX and fuel tank surfaces became detached during flight and gave erroneous data. Improved bonding methods have been developed aad all taak surface measurements on S-IC-3 through -5 will be rebonded. - - Engine area vibration data Sptwious high amplitude, low frequency ~ u t p u bhave invdidaO;(admuch of the vfb~aionand acwstlc date o b t a e d during static firings and the S-IC -1 and S-I@-2 Rights. This problem is concentrated in the engine area, and is caused by the emitter followers and AC amplifiers being overdriven by excessive piezoelectric transducer outputs. The high transducer outputs are caused by high amplitude, high frequency shocks that are generated by uneven engine combustion. To resolve the problem on S-IC-2 though -5, a change was initiated which removed seventeen engine area vibration transducers that had se~aratelvpackaged emitter followere and interconnecting coaxial cables, and substituted seventeen transducers that have integral emitter followers with a higher output capability. S-IC-2 flight data indicated that this change considerably reduced, but did not eliminate, the problem. Another change has been initiated to add a capacitor to the AC amplifier input to block low frequency noise signals. This change is effective for all engine measurements on S-IC -3through -5, and should reduce the high amplitude, low frequency outputs to a level that will not interfere with accurate measurements. - LOX pump inlet pressure measurements The 60B72091-1 transducer used on the LOX pump inlet high frequency pressure measurements has consistently failed during static tests and flight. These failures are apparently caused by physical shock while the transducer is at LOX temperature. These measurements are important for the detection and evaluation of POGO. To determine the best corrective action for this problem, several new measuremente will be made on the S-IC-6 and tested during that stage's static firing. These new measurements include relocation of the subject transducer to a less severe environment, replacement wlth a prototype of a more rugged design, and determination of the feasibility of using existing measurements for detection of POGO-indbed pressure oscillations by increasing the sampling rate. Fuel filter manifold differential pressure transducers -- f mes€igation afthe fuel filter manifolddifferenUalppessure trsn8ducgrbiaashift problem revealed that - D5-1260 1-5 39 �LEGEND 1. YAGI ANTENNA 2. TRANSMITTER 3. -28 VDC 4. VIDEO REGtSTER 5. TO SYSTEM 2 6. CAMERACONTROL 7. TV CABLE ASSEMBLY 8-CAMERA 9. COUPLING LENS 10. IMAGE ENHANCER 11. DC TO AC INVERTER 12. FIBER OPTICS BUNDLE 13. JUNCTION BOX 14. OBJECTIVE LENS 15. PROTECTIVE WINDOW 16. INSULKTION BLANKET shifts can be induced in the transducer by prolonged temperature soak at 130°C. However, after 1200 hours af soaking, test transducers showed no decrease in shift rate with time. Extensive studies by the vendor produced design modifications that were thought to eliminate stress in f i e seneor unft aesem- 40 bly, and thus eliminate the shift problem. Prototypes of the new design, however, showed no improvement. A new design consisting of a single diaphragm with a depasited thin-film strain gage bridge is being investigated. This design m d d eliminate the need for a reference bellows and silicone ofl fill, Also, the new D5-12601-5 �tfansducer would be of an all-welded construction which would minimize diaphragm stresses. Two prototypee of the new design are being built for evaluation. - LOX and fuel loading system During 6-IC-1 checkout, tbe loading system "out-of-lock" monitor that is used ae an interlock in the propellant tankkg computer system (PTCS) operated intermfttently. This waa caused by the loading electronics being susceptible to stage noise under certain conditions. The pr6blem w m corrected by a new design. transfer tests. This problem was corrected by providing untnterrupted power ta the loading syetem. During this reporting period, a change was released to disconnect the checkout (RACS) cables from the loading electronics for S-IC-1 and -2. This prevented instrumentation test,, usfng the RACS system, from upsetting discretes in the PTCS. A change waa also released to provide control of the calibration commands to the loading system from the measuring and R F console in the LCC for S-IC-3 and on, S.IC fv SYSTEM During LOX lotxding at MTF where LUX wm load& Q near 100 percent on the loading probe, the LOX overfill sensor intermittently indicated a wet condition. This was attributed to LOX being splashed onto the overfill sensor due to LOX boiling. This problem wae corrected by moving the overfill sensor approximately four inches forward. The S-IC-2 was the first S-IC flight stage with the TV system lastaIled. The system, which is detailed in Figure 2-18, operated satisfactorily during pre-launch operations and launch. During the SIC-1 CDDT, power to the loading system was lost durfng the power transfer test, upsetting the propellant tanldng c o m p t e r system dfscretes. This was caused by the loading eystem being powered from GSE bueees that a r e turned off during the power The S-fC-2 was the first S-IC flight stage with the film camera system insta31ed. The Position X separatfon camera capsule waa the only capsule recovered, but its fflm was washed out during the first five seconds after separation. It is concluded ehat this FILM CAMERA SYSTEM �was caused by a combination of sun glare and S-II ullage rocket deposits on the quartz protective window, The action necessary to correct this problem will be accomplished on the S-IC-3 and subsequent stages. The W e e camera capsules, that were not recovered, apparently were not ejected, Excesaive temperature and pressure environments immediately following separation -me suspected to have caused faflure of the camera ejection pressurization syrstem. The exact cause of this failure is still being investigated, and changes being incorporated to prevent ita recurrence on S-IC-3 are: from a) Change pneumatic to stainless isteel; b) Add orifices to prevent pneumatic line ruptures from bleeding down the ejection bottles; c) Add thermal insulation to exposed protective cover cables; d) Modify the GSE regulator system such that the ejection bottle can be pressurized to a higher pressure ; e) Add orifices to prevent pneumatic line ruptures from bleeding down the ejection bottles; f) Add thermal insulation to exposed protective cover cablea; and g) Modify the GSE Regulator System such that the ejection bottle can be pressurized tu a higher pressure. Figure 2-19 illustrates the Camera Capsule Assembly. �TELEMETRY SYSTEMS - DC-DC converter and DC power isolator DC-DC converter (60B76 123) and DC power is01a h r (60B76503)failures, due to incompatible production procedures, caused a redesign of the assemblies to provide more reliable componante, Also, NASA disapproved the qualiQcation of the assemblies because of the under voltage rated capacitors used in the vendor design. - ' Remote digital sub-multiplexer (RDSM) -ring a sitnulaW flight test on ehe S-IC-2 at KSC, a 108s of synchronization occurred on the pulse code modulation (PCM) telemetry link. The cause was traced to a remote digital sub-multiplexer (RDSM) output word containing nine logic llzeros" and one logic "one, " while the preceding word contained ten logic "ones. " Under these conditions, the RDSM output caused the digital gate card in the PCM/DDAS assembly to trigger erroneously and inject an incorrect bit into the 30 bit PCM synchronization pattern. Duplication of the problem in the Boeing electronics laboratory indicated that the problem was due to cable capacitance between the RDSM and PCM/DDAS assemblies. A new digital gate card, with input capacitors that masked the effect of the cable capacitance, was incop porated on 5-IC-2 and subsequent stages. This change was not required on S-IC-1 because of the RDSM measurement profile. - Offset Doppler (ODOP)Transponder Boeing has been unable to verify qualification of the Offset Doppler (ODOP) Transponder to the Contract End Item Specification for the S-IC. However, sufficient data was provided on the range safety decoder, and Boeing concurs that the decoder is qualified for the S-IC stage, Figure 2-20 illustrates the ODOP system, GSE/MSE DESIGN S-E PNEUMATIC EQUIPMENT - - S-IC pneumatic console MTF The LOX dome purge maximum lock-up requirement has been increased to 1200 psig and the lock-up pressure recorded from the S-IC-5 static firing was within this limit, A change was also processed to put the low purge on an orificed by-pass circuit to reduce the service time on the regulator. Analysis of S-IC-T static firing data indicated a potential pressure overshoot problem on low h e 1 prepressurization when the fuel tank is at minimum ullage. This pressure overshoot could cause the D5-1260 1-5 stage fuel tank relief valves to cycle. Therefore, a change has been processed to assure that . the stage relief valve will not be actuated under normal conditions. The high failure rate of the helium bottle fill regulator ham been corrected. Andyeie of S-IC-4 and -6 static firing data indicated a potential pressure overshoot problem on LOX prepressurization. Also, calculations based on the static firing and launch data indicated a potential pressure undershoot problem tm fuel prepressurization during engine startup. A change wae processed to corrsot thaae problems prior to S-ZC-3 launch. This change will be verified during the S-IC-6 static firing. - - S-IC pneumatic console KSC All systems met launch mission rules requirements for S-IC-1 and S-IC -2 launches. Subsequent to each launch, one piece of equipment (forward umbilical service) was found slightly damaged due to severe launch environments. Problem areas which became evident during the processing of S-IC-I, and S-IC-2 are: a) A rupture of the GHe Primary Regulator diaphragm would'result in loss of LOX bubbling capability and therefore jeopardize the stage. A change was processed to add redundant capability and was incorporated prior to launch. b) Position of hand ball valves needed more positive control to preclude position change during vibration and allow easy monitoring of valve position. A change that provides position indication and locking was processed to rectify this problem. c) A considerable number of failures occurred in Pneumatic Console solenoid valves. An extensive failure analysis program was conducted in cooperation with the vendor and it was determined that serious seat deformation was occurring when valves were energized for extended periods of time under high pressure conditions. A development program was then initiated to determine the best possible material to resist the seat deformation and meet sealing requixements. Necessary changes have been made and the valves have passed a rigid qualification test. d) Numerous problems were experienced with the primary module Ladewig pilot operated relief valves during qualification testing for 5-IC-1 certification, Redesign of the valves was underW e n and accomplished prior to S-IC-1 launch. Life cycle testing at ~ o e i n g / ~ i c h o uwas d suc43 �cessful. The ncw valve c o a ~ r a t i o nuses a pilot valve: separated from the main valve body by flcsfble hoscs to correct a vibration sensitivit~;problem with the original integral pilot mounting. the subsystems of the S-IC stage handling equipment, At that time, design, maintenance, proof load, and inspection requirement responsibilities were divided between Engineering, Operations, and Facilities for various segments of the total handling equipment. e) Two regulator failures occurred in the LOX dome purge module during CDDT activities for S-IC-2. The failure effects were identical, but the failure causes were not. The f i r s t remla* apparently failed due to operating the module with the inlet manual isolation valve instead of the LCC control. The mpsccrnd rdgtuIator had the same law outlet pressure but had misaligned poppet guide bores that resulted in abnormal wear. A change that provides for incorporation of redundancy, and deletes the failed regulator has been processed. Boeing Engineering was directed, on may 27, 1967 to accept responsibility for the forward lifting linkage assembly and the rotational brace assembly for the Michoud VAB. A production revision record was then established which, (1) provided a new forward hfting linkage assembly, (2) modified the forward handlfw ring b e t f ~ r too proof teet the new forward lifting linkage assembly, (3) modified the existing rotational brace assembly, and (4) modified the existing adjustment linkage assembly. This equipment was used for the first time during lowering operations of the S-IC-10 in the Michoud VAB. Mathematical models were constructed to simulate components, specifically valves and re@lators, in the pneumatic console, thereby facilitating prediction of in-flight operation of these components. Results compared favorably with test data. In addition, studies were made on the necessity of adjusting pipe sizes at the inlet to the pneumatic console to retard the introduction of facility contamination. Research has continued on filtered flow restrictors designed to reduce contamination while still regulating fluid flow. S-IC storage racks The storage racks that were secured to the LUT during the launch of AS-501 were damaged and their contents, including the bulkhead protection equipment, were partially destroyed. It was apparent from inspection of the launch damage that the racks had been subjected to a more severe environment than the environment furnished a s design criteria. f) - - S-IC pneumatic checkout racks KSC Tests conducted using the mechanical automation breadboard (MAB) indicated that the pneumatic checkout racks (PCR) a s presently designed a r e not capable of meeting the customer accuracy requirements for checkout of the S-IC stage LOX, fuel, and thrust OK calips switches. This problem is twofold; first, the ramp rates for pressurization/depressurization of calips systems a r e too high, resulting in excessive pressure change; and, second, the pressuretransducers cannot be calibrated to the required accuracy of 5 -05 percent full scale due t o operation of the transducers a t 16S0F. An engineering change will be processed to eliminate the problems outlined above. GSUMSE TRANSPORTATFON AND HANDLING EWPMENT - - 6-IC stage handling equipment Xichoud VAB H u e r o w rejections against the forward handling ring and the forward Ufthg linkage aseambly brought out the fact that major inconsistencies exfsGed within 44 - An interim change was established to reinforce the rack structural integrity and to provide additional holes for venting the inside of the racks to outside pressures. However, incorporation of this change could not be made to support the AS-502 launch and the launch caused even more damage to the storage racks than AS-501. Damage to the bulkhead protection equipment was eliminated for S-IC-2 since the equipment was relocated from the storage racks to a room in the base of the LUT prior to launch. Subsequent to S-IC-2 launch, the interim change was revised to provide additional vent holes and structural reinforcement on several of the LUT level 60 racks. These modifications constitute an interim fix based primarily on launch damage experienced during the first two launches. The fix is planned for installation prior to S-IC-3 launch. The major problem in redesigning the storage racks * has been in defining the actual launch environment. Adequate data to define the environment has not been gathered because requests that the GSE equipment a r d o r the adjacent LUT structure be suitably instrumented to collect data to define the actual launch environment have been rejected, F i n d redesign of actual launch environthe storage racks to susmen& ia being held pending definition of the launch environment. D5-1260 1-5 ' �SWMSE Intertank umbilical reconnect assembly (a) The intertank umbilical reconnect assembly con- , taias a switch that provides a signal indicating that carrier retraction has been completed. The signal is used to initiate retraction of the swing arm, and its failure can cause mission abort. MSFC requested that a change be submitted to incorporate a redundant "Carrier Retracted" signal source. This was done, the design qualfffed by tercrt, and the chan~qewse fncorparat* ed on the LUT 1intertank umbilical reconnect assembly prior to the S-IC-1 launch. This design change will also be incorporated prior to the launch of all subsequent stages. [b) A failure analysis of the intertank umbilical reconnect locking mechanism, which had failed at KSC during swing-arm tests, disclosed a design deficiency in that an adverse accumulation of manufacturing tolerances could cause breakage of internal parts. Breakage results in the malfunction of the locking mechanism, and prevents a reconnection of the carrier to the S-IC stage. Design corrective action for the locking mechanism to support the S-IC-1 launch resulted in an interim fix, which could be incorporated by rework of existing components. Rework was necessary to support the launch without impacting the schedule. The corrective action taken for stages S-IC-2 and on resulted in a design to prevent recurrence of the failure. (0) The Boeing Company initiated a change for the redesign of the intertank umbilical to include backup capability for the retract system. Th& change resulted from a failure mode and effect analysis and revealed that single - -point failures cwld prevent umbilical retraction. Also, a request for change action has been initiated by S-IC liaison at BATC requesting that the single point failure be eliminated from the retract system. This change has been approved with additional directions to eliminate single point failure modes in the retract and reconnect systems. dl During the extension of swing arm number 1 at KSC, following the S-IC-2 overall swing arm test, the intertank umbilical inadvertently became unlatched from the retracted position. The event went unnoticed durfng the remainder of arm extension a d as the gwlng arm approached full extension, the umbilfcal struek the stage. Minor damage, requiring no repair, was experienced by the stage, but the umbilical LOX lines were damaged to the extent that partial replacement was required. Subsequent investigation revealed that the ability of the latch to hold the umbilicd in the retracted position under shock conditions wae marginal, Therefore a change was initiated which provided a redesigned latch to prevent a recurrence of the problem. Forward umbilical carrier problem at KSC on S-IC2- Two valve-type umbilical ooupZings on the S-IC forward urnbiliaal ground oarrier did not mate prom perly with the flight-half couplings. This resulted in partial*closureof the valves within the couplings and restricted flow. Indications were that hardware nonconformance (currently undefined) prevented the ground carrier from fully contacting the vehicle plate. The problem with the couplings was corrected by a change that installed a spacer behind the ground-half couplings thereby assuring that the internal valves are fully open. With MSFC and KSC concurrence, S-IC liaison generated a change, that called for replacement of the poppet valve couplings with straightthrough couplings on S-IC-3. The straight-through couplings should eliminate any problem of flow and lock-up pressure associated with the forward umbilical service unit. However, with the bowed condition of the forward umbilical flight plate, shimming of the straight-through couplings may be required to prevent leakage at the coupling seal. The closure problem of the coupling valves will not occur on S-IC-4 and subsequent stages because couplings used on the forward umbilical for these stages are not susceptible to this problem, However, the basic cause of the problem, improper umbilical carrier mating, is still under investigation. MISSISSIPPI TEST FACILITY S-IC-5 static firing - While preparing for the S-IC-5 static firing the stage fuel emergency drain duct collapsed during the fuel loading portion of the propellant load test. Investigation revealed that a negative pressure of as much as 12 psig was being developed in the facility RP-1 fill and drain system by a recirculating procedure that was being used for cleaning purposes. Although the same procedure had been used on previous stages (S-IC-T and S-IC-4) the condition was not detected because these stages were equipped with heavy-walled I.060'3 drain ducts. The wall thickness of the 5-IC-5 duct was only 03Zrt. After additional investigaffon and experbentation, the ta*g Procedure was revised to eliminate the recirculation mode, a nitrogen preesurization system was installed in the . �facility RP-1 lines, md the lines were instrumented to give a continuous r e d o u t of system pressures, - During the second propellcant load test of the S-IC-5 the LOX tank ullage pressure was observed tu go negaifve about 0.3 psig for a few seconds after two-line LOX bubl~lingwas initiated. This negative pressure was produced when the ullage volume was suddenly chilled by LOX geysering into the tank from one o r more of the partially filled suction ducts. The tanking procedure w3s changed to close the vents and pressurize the LOX tank to 3 to 4 psig before start of bubbling, This procedure was used eutcessfully on firing day. However, the auxiliary vent had to be cycled 38 times in maintaining the ullage pressure between 3 add 4 psig. Experimentation is under way at MSFC (S-IC-T at R-TEST) to devise a procedure that will suppress geysering without the necessity for cycling the vents. Valve position indications from the pneumatic console were lost momentarily four times during the S-IC-5 static firing. A post-firing examination disolosed no broken wiree or loose connections in the power circults, and a change was initiated to provide a redundant path for indicating power to the pneumatic consoles at MTF and KSC, Oiict a) b) 46 Support KSC An engineer from Michoud has been on site atKSC to provide direct coordination between Boeing Schedule I (Test Requirements) and Schedule Il? (Test Procedures),. This work involves assisting in the review of approximately 150 test procedures per stage, the resolution of commenta from Michoud and KSC on approximately 50 test procedures per stage, and the preparation of the detailed audit of test procedure compliance with test requirements. This support will beprovided to KSC as long as it effectively contributes to the S-IC stage program. Technical support was also provided during the prelaunch tests and during the actual launch countdown of AS-501 and -502. This support was provided through participation in a team stationed in the central instrumentation facility at KSC and through a team stationed in the Huntsville operations support center at MSFC. For the CDDT and launch of the AS-50 1 and -502, continuous support during the final 24 hours of countdown was provided for KSC from Michud, - Preoperational safety review An S-IC preoperational safety review for the S-IC-1 was conducted at KSC during the period July 5 through August 11,1967. The review team consisted of members from Boeing, General Electric, International Business Machfnes, and Rocketdyne. Test procedures affecting the S-IC stage were reviewed against safety criteria that were developed to determine whether or not unsafe conditions could occur as a result of executing the procedures. A total of 159 test procedures were reviewed, resulting in 119 safety problems reports. All 119 have been closed out. - KSC test requirements coordination Revision E to "Specifications and Criteria for S-IC Stage Prelaunch Checkout and Launch Operation at KSC" (D5-13618) was released during FY 1968. This revision incorporated committed changes and MSFC comments. The majority of these comments concern level of detail and the addition of primary requirements for tests being conducted in excess of the existing requirements. These comments were discussed with MSFC on December 19, 1967, and The Boeing Company agreed to make many of the changes to encourage a more uniform MSFC acceptance of document D5-13618 as KSC test requirements. - AS-501 and -502 GSE launch damage As a result of the launch environment, some GSE items on the mobile launcher were damaged. The following table is a brief asseslsment of this damage: S-IC-1 S-IC-2 a) S-IC pneumatic console Valve manifold assembly damaged No damage b) Pneumatic checkout racks No damage No damage c) Prevalve accumulators No damage No damage d) Aft umbilicals Major damage No damage e) Intertank umbilical Minor damage Control box panel missing Miaar damage No damage Forward umbilical ' D5-1260 1-5 �I' Intertank " 3) Thrust Minor damage Minor damage Minor damage Minor damage No drtm structure h) Heat shfeld storage No damage No damage i) Thrust structure No damage vertical internal access equipmetlt storage r a c h No damage j) Forward skirt Moderate Moderate &ten%mcear dam ~ W W equipment storage racks k) Fuel tankupper bulkhead protection equipment storage racks 1) LOX tank upper bulkhead protection equipment storage r a c h Racks heavily damaged Totally destroyed Racks heavily damaged Racks heavily damaged damaged Totally destroyed A damage assessment for tbe S-IC umbilical equipment that supported the S-XC-1 launch was aecomplished* The three AFT umbilical carriers sustained major damage resulting from the f a u r e of the tail service mast protective doors. The intertank reconnect assembly and the forward umbilical carrier euetafned only minor damage, A change w a initiated ~ a s a result of thie assessment. This change provided additional fasteners for the intertank reconnect aseembly control box covers to prevent the covere from beearning detached as Ls reeult of vibratfon. A preliminafy assessment of the damage euetaiaed by D5-12601-5 A detailed analysL of this damage L contaiaed in dacument B5-%584& "MobBa Launcher No. 1 Q8E Damage - Assessment and Corrective Action Recommendations," for the AS-501 launch and the follow-on document, D5-13842-1, for the AS-502 S-IC-2 launch, ENGINEERING TEST PROGRAMS During F Y 1968 test activities were directed toward the completion of the reliability program, qualification program, and resolution of design data problema and discrepancies identified during manufacturing, ~t;;Lt;lD Xi&%, a 4 6-IC-I, BXXd 8=XC43 I w ~ suggsst ~h sper&aaaa, rn) Intertank vertical Heavily internal access equipment storage racks the 8-IC umbilical equipment during the AS-502 launch was conducted. The three Aft umbilical carriers sustained no visual damage and appeared to be d e quately protected by the redesigned blast shields that were added to the t a i l service masts following the AS-501 launch. The intertank umbilical reconnect arssembly sustained moderate damage resulting from heat and vibration, but there was no major structural damage. The forward umbilical carrier eustained no apparent damage. At the beginning of the reporting period, Engineering Laboratories had 59 tests on hand. During the year, 355 tests were received, and 331 were completed. Testing is divided into categories of reliability, qualification, and development testing, and f aflure analysis. The High Pressure Test Facility, which experienced approximately five months of down time due to a high pressure line failure, resumed operations in August, 1967. To minimize the impact of the loss of the facility, six tests were conducted at the adjacent Michoud/Chrysler laboratory facilities. RELIABILITY TEST PROGRAM The reliability test program began the report period with six testa scheduled for a December 6, 1967, completion date. During that period, four teats were received, one was cancelled, one was reopened, and nine were completed. Reliability tests completed during F Y 1968 include: R401- Pressure relief switch R415 Redesigned outboard engine GOX line assemblies R427 Engine purge system regulator R22Z Thrust OK distributor -- 47 �R409 R465 R402 R4 11 R413 -- Redesigned Valve-to-tunnel duct aseembly feeder duct - Upper hot helium supply duct GOX GOX -- lnboard GOX line assembly Uppcr outboard GUX duct assembly OUALIFICATION TEST PROGRAM During the reporting period, qudiflcation testing for 220 compotients was successfully completed, increasing the number of certified components by 208 from 1103 to 15I I, sixty components r e m h to be certified (see Figure 2-21), All S-IC-1 and S-IC-2 stage and stage-peculiar GSE hardware was qualified prior to launch, and all S-IC3 stage and stage-peculiar GSE will be qualified prior to launch. At the beginning of this reporting period, the engineerirrg laboratories had eIeven qualification tests on hand scheduled for completion during December, 1967, During the period, sixteen additional tests were received, one was cancelled, and nineteen were completed, leaving seven tests to be oompleted, Also, the piece parts qualifioation test, P24 (quality assurance inspection of MBR37496-9 and MBR3749610 relays), is an open end item with lots tested on a periodic basis as they are delivered. DEVELOPMENT TEST PROGRAM During F Y 1968, 208 Development Tests were initiated, and 213 were completed. Engineering Laboratories supported the AS-50 1 mtowlmmr~ S-IC CONTRACTOR QUA1TEST SUMMARY OnmlOltOU1WEl' ALL CATEGORIES +--. Figure 2-21 48 -- S-fC Qualificatian Test Summary Dti- 1260 1-5 �lnunch by conducting three development tests. Five development tests were conducted in support of the AS-502 lnunch. Subsequent to the S-IC-2 launch, Engineering Labora- torirs also participated in the search for cause mtl solutions of problems encountered during the flight of AS-502. Durlng FY 1968 twenty-eight development testa that lcd to desibq changes were conducted. Eight development tests that deal with current problems were in progresa at the end of the reporting period. FAILURE ANALYSIS TEST PROGRAM During the fiscal year 90 faflure analysis testa were completed. INVESTIGATION OF DEEP-FLAW EFFECT IN S-IC TANKAGE Problems on the S-II stage focused attention on all S-IC stage pressure vessels that a r e proof-tested at room temperatures and a r e used at cryogenic temperatures. The problem involves the fracture toughness of tank material in the presence of a deep surface flaw. A fracture toughness test program has been initiated in Seattle to investigate the deep-flaw effect in 22 19 aluminum with a scheduled completion date of July 1968. Previously, an evaluation of all S-IC pressure vessels had been conducted by the structural development unit in Seattle. Based on existing data, the S-IC propellant proof tests were found to be adequate. Results of the current test program a r e expected to verify this evaluation. S-IC SYSTEMS A N D STUDIES STAGE SAFETY STUDY The stage safety study was conducted for S-IC-2 through S-IC-15 stages, a t MSFC1s request, to determine whether the stages would be safe at KSC for a seven-day period during which RP- 1 fuel is onboard, stage electrical power off, and GSE electrical power on o r off. "Safe" was considered to be a condition that would assure no physical o r functional damage to stage systems o r subsystems. Damage was considered to have occurred if the design limits, tolerances, o r specifications of a stage, system, o r subsystem were exceeded. The study indicates that the S-IC Stages a r e "safet1 when certain conditions exist as' defined in the study. S-IC ENGINEERING SYSTEM SAFETY PLAN Safety Engineering i s preparing an, "S-IC Engineering Safety PlanrTwhich will develop and implement a system that identifies relevant goals, requirements, controls, procedures, responsibilities, methods of accomplishment, and schedules for systems safety engineering. A preliminary copy of this plan was reviewed and commented on by affected organizations, and the estimated final release date is July 1, 1968. SPECIFICATION COMPLIANCE STUDY All S-IC requirements necessary to assure astronaut safety, stage integrity, and achieve end conditions of flight have been designated a s "Man-Rating Requirements", and will be verified as completed through an S-IC-3 specification compliance study. The S-IC contract end item specifications and Saturn interface control documents have been reviewed and a l l applicable man-rating requirements identified. Documented verification of compliance is being established by reviewing engineering and test documentation to assure that the identified requirements have been met. This study will be published as document D5-13874, "Specification Compliance Study for S-IC-3," which is scheduled for release on June 28, 1968. S-IC STAGE DAMAGE PREVENTION STUDY Document D5- 13704, ITS-IC Stage Damage Prevention Study," was completed on April 12, 1968, and is currently being released. This document presents the results of a study that was performed to establish and recommend dispositions of ground support equipment failures that could cause S-IC stage damage at MTF, The original findings were based on the S-IC4 configuration. A formal "Fault Tree Analysisf1wae used to identify areas of concern. One hundred twenty-one potential hazard areas have been identified of which 93 have been satisfactorily resolved with the remaining 28 still under study. A follow-on study to update the findings for the S-IC-6 configuration is in progress and will be documented prior to static firing. S-IC STAGE STORAGE S-IC stage storage requirements have been prepared and forwarded to MSFC for approval. MSFC standards 492 and 500, giving S-IC stage storage specifications, were received as information from MSFC, and have been reviewed. In several areas, these standards a r e more stringent than the Boeing prepared requirements. Major differences a r e in the �basic processing program modifications were incorporated, and PERT charts were released in about one half the time required for the S-IC1 flight. Data handling team interface review meetings were held to strengthen the overall communication network between the various flight evaluation organiz;ationa. area of ambient humidity, maintenance of contaminant levels and restriction of partfeulate material, and, in general, cover long storage periods* The fin& agpmvod requirements for storage will become part of the CEI Specification Part XI, FllGHf NAUIATION PROGRAM Test data requirements for analysis of the AS- S-1C.l Flight a) 502 CDDT, countdown, and launch were compiled and coordinated with the MSFC Mission Operations Office and MSFC Com~utationLaboratory. Inputs were made for fnclu'ion in the NASA Program support requirements document and the MSFC processed data requirements document, Attempts were made to obtain installation of additional instrumentation at KSC for measurements of the launch environment and its effect on the GSE. This was not successful for the ASS02 launch, but efforts are continuing for the S-IC-3 launch. Flight Ev aluat ion Preparations In prcpriration for tho S-101 flight, a complete practice run was necornplfshed using the S-IC-3 static firing telemetry data as the data bank, The practice*run provided a successful verification of our capability to reduce, process, and analyze the S-IC-l flight data. Also, a complete set of flight predictions were calculated and documented. These predictions were used to provide a rapid assessment of the S-IC-1 flight performance by identifying mearsurements that were significantly different from those anticipat&, b) Flight Evaluation The S-IC- 1launch occurred at 7:00:0 1 a. m. , EST, on November 9, 1967. The Boeing flight evaluation team participated in three presentatfon meethgs which reviewed the flight d a t a The required twenty-one day report was submitted to MSFC a s scheduled, on December 5, 1967. Generally, the AS-50 1 flight met all mission objectives except a s specified in the BoeingSixty Day Report, document T5-7000-1, which was released as scheduled on January 11, 1968. The report evaluated the performance of the first flight of the S-IC stage. The flight prediction document, was released on March 11, 1968. This document listed the predictions for S-IC-2 flight measurements. b) Flight Evaluation S-IC-2 post-flight activities, including the reduction and processing of the raw telemetry data, followed the PERT plan as closely as possible. The BERT completion times of some items were not met due to late delivery of data tapes from MSFC, and special analysis of the POGO problem, which impacted the entire processing effort. Data from the TEL 4 ground receiving station was used as the primary source for the PAM and FM data until the POGO problem became evident, A 2 cps "wow and flutter" error was found in this data, and the Central Instrumentation Facility ground receiving station data was used. S-IC-2 Flight a} Flight Evaluation Preparations Preparation for the S-IC-2 flight included such activities as certification of the basic data processing program using S-IC-2 flight readiness test data as input and verification of the stage telemetry configuration. Standard basic processing analysis program work was completed on schedule, As a result of prubIems encomtersd on the S-TC-1 Bight, several 50 Processing charts were released daily aa a tracldng method for the flight processing. These charts were released through L+14 days as required. A11 b e i n g contractual data deliveries were completed on or before the required delivery dates. The S-IC-2 data quality and delivery schedule was generally better than that for the S-IC-I. launch, As a result of pereonnel training after the S-IC-1 D5-1260 1-5 �ght and improved activity schedttlbg, the numbcr of aperture cards made for the S-IC-2 flight reduced by 33 per cent from the $-IC-1 t. a result of a problem encountered Sn the PCM a from the S-IC-2, a new formatting &ahue for PCM data was designed. The L+1, L+8, and L+14 day presentation material for the SIC-2 night were delivered on schedule to the MSFC flight svduatem working gmup FEW^ ohtlimas, The boejlng be21 dw input to the FEWG AS-602 report waer submitted aa scheduled on May 9, 1968, The L+60 day report T5-7000-2 was released, as scheduled, on June 28, 1968, V.7 PH. STAiNLESS STEEL USAGE SURVEY A Boeing survey is being conducted to determine all 17-7 PH steel parts used on the 5-IC stage that are reliability critical per document D5-11910. Fiftyfour parte made from this alloy were f~und, These are urrd In c~mpntaa@Xirat& h tat& dssmctat~ A matsix sf the pmoesssrr tur$ proceesing wed h fabrication of these parts is in preparation, to launch, that are dispositioned "use-as-is. " The procedure requires both NASA and Boeing technical and contract signatures to validate the waiver. All waivers are then documented in the appropriate Part I CEI Specification subsequent to vehicle launch. Ten 5-6-2 waivers were processed, approved, and incorporated hta the Part I CEX Specg$cation using this procedure. INTERFACE CONTROL DOCUMENTATION (ICD) AND INTERFACE REVISION N O T E E (IRN) STATUS OF BASIC ICD'S As of May 16, 1968, there were forty-five basic ICDta applicable to the S-IC stage, of which thirty-three are applicable to the stage hardware, eleven are applicable to the GSE, and one is common to both stage and GSE. All ICD1s a r e identified fn the May 1, 1968, issue of MA-004-002-2H, "Saturn V/S-IC Interface Control Documentation Contractual Index and Stabs Report. l t pa* CONTRACT END ITEM (CEI) SPEClFlCATiONS The Part II S-IC CEI Specification, S-IC-3 through S-IC-10, has been prepared and is currently being reviewed by NASA. This specification will be incorp r a t e d into CPIF Contract NAS8-5608, Schedule I, subsequent to negotiation and NASA approval, and when it is approved, will serve as the basis for configuration definition and a c c e p h c e testing of Stages S-IC-3 through S-XC-10. Ttre S-IC-4 was delivered to the Customer at Michoud with one government and two contractor CEI nonconformaaces for which no corrective action was required. Of these nnnconformances, eleven MSFC and twenty-four contractor qualified electrical comportents failed to fully achieve electromagnetic interference test requirements under MIL-I-618D. Also, voltage fluctuations (transient@ in excess of the end item test plan limit8 (t 14 volts) appeared at one of the monitored electrical circuit mints during power application add removal sequences. During the fiscal year, a wafver procedure was establlshed to cover wncodo~mancee,evidenced prbr D5-1260 1-5 Of the forty-five basic ICD1s applicable to the S I C stage and associated GSE, forty-one were officially accepted by Boeing, three have not been received, and one is not acceptable at this time. The three ICD1s not received are flight sequence programs for AS-508, -509, and -510, The ICD not acceptable to Boeing is the interface between the LUT and the S-IC access and bulkhead protection equipment storage racks. An administrative change propos d, which defines the changes required for compatibility with S-IC stage documentation, has been submitted to NASA. On August 8, 1967, Boeing initiated the use of record ECP's for the purpose of contractually accepting IcD/ ntN1s if they are compatible with S-IC Stage and CSE hardme and documentation. ~~~~d E C P I ~~ - 0 0 0 1 through R-0073 have been submitted to MSFC through May 16, 1968. RELIABILITY ENGINEERING RELIABILITY ANALYSIS - Documents'D5-12572-1, Its-IC System Design Analysis Propulsion/Alechaaical,'~and D5-12572-2, llS-XCSystem Design Analysis Electrical/Electronfcs ,'I were each updated Mce during this reporting period. These updates reflecEed failure mode and effect analysis, both - 51 �1 propulsion/mcehanical and electricallelectronics , for S-IC-3 and -4. Other imporbtnt S-IC reliability documents that were relemed during the reporting period, and the purpose for the release, are: 4 Document D5-11910, ,"Saturn S-IC Reliability Status Report,ll -Two updates were made, one to add additional status on reliabiliQ program elements, and one to add S-IC-4 stage release. b Dacumefit D5-31964-1, "Saturn S-IC Stage Reliability Analysis Record. "-Updated twice during F Y 1968 to report predicted and assessed reliaWlity for S-IC-3 and -4. 6) Document D5-13693, "Hydrogen Explosion Hazard Survey." -Updated twice to report that no ignition source is present in the interstage area that is sufficient to detonate an assumed hydrogen atmosphere. d) Document D5-11954, llSaturnS-IC StageReliability ~' Assessment and Prediction P r ~ g r a m . -Revised once during the year. This document contains the methodology used to apportion reliability goals and describes in detail, the Saturn S-IC reliability information system, 8) weekly I1FailureStatus SummaryM(unresolved failures) for program corrective action, the Michoud Reliability Data Center has initiated a "Top Priority" report for each scheduled launch. This report includes only those failures that could impact launch. If program corrective action cannot be implemented prior to the launch, the problem is submitted to the BoeinghIichoud UER/ CER Assessment Board for launch impact assessment. This "board" is chaired by the S-IC Chief Engineer with representatives from Boeing Quality and Reliability Assurance (Q&RA), and Product Assurance. Equipment Ouality Analvsi8 The equipment quality analysis effort was expanded during F Y 1968. This was the result of increased emphasis on product quality initiated in 1967. Emphasis has been placed on the analysis of reliability critical components. Additionally, this area has been expanded to provide the quality maintenance testing required by contract change order MICH-723. This combination of equipment quality analysis and quality maintenance testing constitutes an ambitious schedule of in-depth testing and analysis of "criticals1hardware. During the fiscal year, 111 Equipment Quality Analyses sad six Quality Maintenance Testa were performed. A summary of this activity follows: a) Document D5-12789, "Design Analysis for S-IC Malfunction Detection System. "-Updated once to reflect release of S-IC-4. This document cmtafns the necessary analyses and data from which the S-IC design requirements for a malfunction detection system may b t determined. ' In addition to monitoring receiving and subassembly discrepancies, major emphasis has continued on monitoring and evaluating in-service faiIures that occur on stage and GSE hardware during post-manufacturing checkout, static firing, and post-static checkout and after delivery to KSC . In addition ta tracking each in-service failure in the 52 ........................111 Number of EQA's performed andclosed..........................,... 92 ................. 51 Design C hasge ................. 5 Process Change.. .............. 5 Quality Control Improvement.. .. 31 1) With no anomalies.. 2) With anomalies resulting in : Failure Analysis Continuow emphasis has been placed on the S-1C Failure Analysis program. A total of eighty-two failure analysis test were completed during the reporting period. Operating procedures were revised during FY 1968 t o improve processing and analysis of failed hardware. Number of EQA's performed, during F Y 1968.. NOTE: Some EQA's resulted in more than one type of change. c) Number of EQAts performed remaining open ......................... d) A11 QMTts performed are open. e) Number of hardware problem analyses performed F'Y 1968 f) Number of discrepancy checks idsued FY 1968...*.r..rrea.*.e.-o..*..e=~...*. 19 ............. 138 39 D5-12601-5 �Oata Gallect~on artd Analysis During F Y 1968, 525 special computer printouts concernirrg faifure data were supplied to requesting organfzafioas by the Launch Systems Branch Reliability Data Center. These special printouts were reqaired to @upportsuch varied actfvitfae m product mcsaurmca, hurnaa engineering, and logistics. L A totrh of 789 Boeing Investigation and Corrective Action Requests (BICAR") were initiated by the Launch Systems Branch or assigned to Bming by NASA during F Y f 968, 8even hundred Urirty-five of these werecloered, and 54 r e m a n open and are programmed for completion aMf closeout during the first quarter of FP 1969. Continuous effort is being expended to isolate repetitive failure trends. Some of these collective analyses have resulted in further laboratory analysis and/or design corrective action, The requests for design corrective action are included in the BICAR statistics above. A total of 84 NASA "ALERTS" (problems experienced by other NASA centers and contractors) were received and evaluated for 6-IC impact during FY 1968. Seventyfive were closed; nine remain open, Refiability Audits The results of the FY 1968 reliability audits of compliance with the reliability requirements as defined by D5-11013, "Reliability Program Plan," and related documentation have been published for the first three quarters of FY 1968. These three quarterly "Reliability Program Status" reports were D5-13747-3, D5-13747-4, and 05-13757-1. The "Reliability Pro=am Status" report for the fourth quarter FY 1968 will be published after the end of the fourth quarter and will be designated D5-13757-2. The review included analysis of specifications, qudification, receiving inspection, functional test, vendor surveillance, and failure history. As a result of the review, recommendations were made for strengthenina; product quality of piece parts and standards. These recommendations resulted in tighter receiving inspection, increased vendor surveillrmae, and inoremced equipment quality analysis activity. Also, an engjneering review board recommended action on 34 critical piece parts for either new specifications, revised specifications, or higher level of qualification, Those recommendations were approved by the S-IC Chief Engineer and are in process of being implennenbd. Reliability Analysis Model Work continued during this report period in support of the reliability analysis model. This model delineates ground rules for providing S-IC stage reliability data I Reliability to MSFC as an input into the MSFC Level X Analysis Model (RAM). Failure effect analysis loadsheets, non-critical cables lists , criticality determination loadsheets , symbolic block diagrams, and engineering critical components lists for S-IC-3 and S-IC-4 have been completed and transmitted to MSFC. Faiture Management by UCR Task Force and Assessment Board During FY 1967, a task force was established to assure that all Unplanned Event Records (UER) and Unsatisfactory condition Reports (UCR) were properly dispositioned , failure analyses completed, program corrective actions taken, and flight readiness actions specified prior to the AS-501 flight. Major functions performed were: a) Classification of all S-IC program failures by their criticality as assessed in relation to S-IC-1 launch effect; b Establishment and implementation of a workable failure and failed hardware activity tracking system; and c) Support to the UERNCR Assessment Board, which was established based on the task force finding that program corrective actions could not be ,completed on all failures in time to meet the launch date. Product Quality Survey Work continued on the "Product Quality Survey" during this report period. This survey, which was initiated during FY 1967, reviews and updates existing GSE failure mode and effect analyses. This updating covers hardware and time intervals not previously analyzed, identifies single failures that could cause abort, and identifies single failures that could cause loss of stage vehicle o r crew. As a part of the product quality survey, an in-depth review was made of all $-IC stage piece parts and standards, This review was conducted by Engineering, Quality and RellaE>ifityAssurance , and 0perat;fom. f35-52601-5 Assessment Board members were the S-IC Chief Engimer ,Q&RA representative, Product Assurance manager and the UCR task force manager, , 53 �I The itshiesamcnt Board reviewed all w e s o l v e d failures and evvluatccl the risk each might have on the AS-501 launch and flight to assess Boelng's 8-IC flight readincss position. R e l i a b L ~Program Ptesentations The monthly S-IC reliability program status was presented to NSFC on February 19, March 18, aad April 16, 1968. The general outline of these presenWions is as follows: Activities of relihility and ssordinaaon sf b) c) dl e) 0 g) h) committcre; Summarize ECP's initiated, c h w-e d , o r s t o ~ v e d because of reliability activities; -- Summary of ECP1s reviewed by reliability organizations ; Failure reporting and correction action; Human factors; F M ~ E A ' S ,reliability predictions and assessReliability test; P a r t s program activity; j) Materials and processes activity; Boeing selected areas from 65-18 history approach, philosophy; and k) Significant changes in program o r organization. I) Since July 1967, the reliability coordination committee has held bi-monthly meetings to implement corrective actions required to eliminate S-IC reliability deficiencies , all of these actions were completed by December 29, 1967, Two NASA/Boeing meetings concerning reliability program deficiencies and planned corrective actions were held August 91, 1967 and September 5, 1967. These meetings presented The Boeing Company's positiotl and planning to implement an effective S-IC reliability program, Another meeting was held on December 7, 1967 to report the status of the 6-IC reliability program and discuss associabd prablems. Growth of Assessed Reliability for S-IC Figure 2-22 depicts the growth of assessed reliability for the S-IC stage. MANUFACTURING DEVELOPMENT The Manufacturing Development organization, a part of the Boeing/Michoud Operations organization, supports manufacturing in all areas necessary for the production of S-IC stages. This organization works closely with Engineering Design and other technological groups, and maintains constant surveillance on new trends in materials, design, and techniques that a r e applicAle to the Boeing/Michoud S-IC program. WELD DEVELOPMENT TANK SKtN TEE STIFFENER CRACKS At Michoud Engineering's request, a weld repair program war, devised to repair tee stiffener web cracks. Since minimum heating in skin membrane was desired, the following heat sink methods were employed on simulated repair weld panels: copper chill blocks were placed adjacent to the manual 'i'ungstenInert G a s (TIG) repair on ofie side of the skin membrane, and dry ice was held in place on the opposite side of the skin membrane. As a result, heat-affected membrane areas of the simu-. lated repair weld did not exceed 300°F, and this repair procedure was adopted in lieu of riveted doublers for future tee stiffener crack repairs. 6UX DUCT LINE MODIFICATION Figure 2-22 54 Growth of Assessed Reliability1-S-IC Stage Manufacturing Development was requested by Michoud Engineeriag to assist in high priority prototype weld fabrication of an S-IC GOX line duct. This work bvolved manual ETA (Gas TungsWben Arc) D5-12601-5 �1 I welding of A-286 alloy with Hasteltoy W filler wire DIAPHRAGM TEST HARDWARE ' and was initiated after reliability tests [static pressure plus induced vibratory stress) resdted in fillet weld failures. Engineering redesigned the COX duct line by deleting four fillet welded gussets qnd replacing them with an attachment flange with 400 p r c e n t penetration single ves weld joints, yabrlcatfon of needed weld tooling and establishment of welding sequence was then undertaken by Manufacturing Development. Upon completion of this redesign, reliability testing established acceptability of the redesigned assembly, As a part of Boeingls company-sponsored activities at Michoud, two flat bulkhead tank assemblies were completed this year in support of Boeing/Nmtsville Engineering. Fabrication of these tanks was part of a program initiated by Huntsville to determine. the feasibility of replacing forward S-IC bulkheads with flat diaphragm bulkheads. MACHINING AND FORMING SATURN S-rC REPAIR WELD HISTORY ELECTROMAONETIC C Q ~ LREPOTTING AND MANUFACTURING FACILITY ESTABLISHMENT STUDY Repair welding a t Miehoud is monitored by the Manufacturing Development organization. Records of repair weld frequency include the S-IC-15 stage. Figure 2-23 is a data plot, which includes 1968 repair weld frequency. Accumulative percentage of required repair welde through March 1968 was 0.605 percent, This compares favorably with the March 1967 average of 0.614 percent, During the reporting period, a repotting procedure, including tooling, was established for repairing o r buklding new 4-1/2-inch diameter electromagnetic coils that a r e used with the high-energy capacitor discharge unit to correct contour distortions on the S-KC. Damage occurs to these coils when part of the polyurethane potting compound separates from the coil or when a dielectric breakdown of the pot- I AlRS/100" OF WELD) Figure 2-23 D5-12601-5 S-IC Repait Weld Frequency 55 �1. ting occurs. f n thc past, dnmaged forming coils wcrc sent lo itnother fscility to be repairad. This usuaily took rtbaitt three months. I t is now possible to repair a rlamnged coii at X-lichoud in five days. It is also possible to produce new coils to alleviate tkc pmscnt shortnge and to evaluate coil efficiency for various dcslgns, close tolerance requirements, an orbital fIaring concept developed by NASAfMSFC was evaluated. This concept, which utilized a cone and die cartridge assembly may alleviate the misalignment problem encountered with the conventional Leonard 3CP machines. Its use will possibly enable certification of only one machine oapable of ueing varying tube sizes. STRESS RELIEF WITH VlBRELlEF MACHINE CHEMtCAL PROCESSES An evaluation was made of sonic vibration for s t r e s s relieving metal parts warped by machining, welding, o r hcnt treating, This was done to find a method for expediting the flattening of base heat-shield panels warped during test firing of the S-IC-4 stage s o that these panels could be used on the S-IC-8. T e s t s conducted using a Vibrelief machine manufnctured by Lodding Engineering Corporation were unsuccessful; therefore, sonic vibration for s t r e s s rclicving metal parts of the S J C vehicle i s not considered practical a t this time. Further research on this method i s necessary to expand its potential for future production use. IFFU US ION BONDING CAPABILITIES AT BOElNGlMlCHOUD The growing importance of diffusion bonded assemblies in aerospace applications prompted a study of limitations and capabilities within the Boeing/ Michoud facility. One of the objectives of this study is the development of a sub-scale facility in which various concepts relative to the production of a true diffusion bonded assembly may be evaluated. Successful solid-state diffusion bonding of Ti-6A1-4V (titanium alloy) to itself has been achieved with little difficulty. Solid-state bonding of 6061 aluminum to itself has also been achieved with the use of a copper interleaf. Efforts a r e continuing to diffusion bond aluminum to itself without the use of an interleaf. As a part of this effort, an evaluation is being made of a process by which component specimens a r e protected from atmospheric contamination by being totally immersed i n a cleaning solution a t each stage of the cleaning process. While still immersed in the final cleaning solution, the components a r e transferred to a vacuum chamber within the furnace. This chamber, containing the same solution, is then sealed, pumped out, and back-filled with argon. Diffusion bonding then takes place in this argon atmosphere. AIR POlLUTlON CONTROL Many Boeing suppliers are located in Los Angeles County, California, where a i r pollution control regulations have been put into effect. Since there is a trend toward increased legislation regulating permissible contamination, Manufacturing Development is conducting a survey of current control regulations and legislation. Boeing/Seattle has already found it necessary to modify one process specification to meet Los Angeles County requirements. Possible replacement processes for Boeing specifieations that do not meet Los Angeles County air pollution standards a r e being investigated. HIGH TEMPERATURE RESIN FOR ELECTROMAGNETIC FORMING COIL ENCAPSULATION Several materials have been examined for electromagnetic forming coil encapsulation. Criteria for evaluation included high-impact strength, hightemperature stability, and a hardness comparable to cured polyurethane resin, the material that is used to pot coils for ambient use. Representative formulations of the following three different types of material have been selected for further development: a temperature-resistant epoxy resin, a high-. : strength silicone rubber, and a high-temperatureresistant polyaromatic. ' EVALUATION OF ZlNC PAINT COATINGS FOR STEEL TABLES IN VAB A zinc paint coating was applied to one section of a steel turntable in the VAB and was found to resist the corrosion that normally occurs. Plans have been made to apply this coating to the three turntables in the VAB. This will result in a labor Cost savings. . �reinforced with advanced filaments, such as oron, in lieu of normal glass fibers. The result is a high-strength, high-stiffness , low-weight material with major structural applicstiom Fabrication data and experience on a laboratory basis is being gained for possible use e stages bepond the S-XC-5. Tensile and flexural test p-la of boron filaments in an epoxy matrix have been fabricated and tested, and continued evaluation is planned for combined boron filament/gtass cornpoaites where advantage can be taken of the high strength of boron filaments and the low c w t of QbaOnen, . ELECTRICAVELECTRONICS SHEET M PROGRAM DEVELOPMENT SYSTEMS During this reporting period a product analysis function was established in the source control group. As a result, undesirable trends, potential problem areas, and deficiencies, can now be detected by review and evaluation of Equipment Quality Analysis ( E W )reports, Unplanned Event Records (UER1s), fdlus%/defecl data, receiving fmpe~Woa~ ( I ~ o F E B I , laboratory reports, and other pertinent data, and action as necessary will be initiated to correct the same. E MOLDS FOR ELECTRICAL CABLES During the reporting period, a technique was devefoped for polyethylene molds to be produced for use in electrical cable production. A .O4-inch thick polyethylene molding materid i s used since it is semi-transparent, semi-ridged , i s eaaily trimmed, and requires no mold release. The molds axe made on a commercial RAY-VAC vacuum-form machine, which has a 24 by 24-inch capacity. The sheet polyethylene, while hot, is formed over a die by pulling a vacuum under the mandrel. Significant savings can be realized by using sheet plastic molds since they can be reproduced at the rate of one per minute on the RAY -VAC machine. IMPROVED MANUFACTURING TECHNIQUES During FY 1968, Boeing/Michoud worked with tool eupaliesa ts d w e I ~ pa z q y inapx~vedmmubacW= imVB be@n komqusB * T h s ~ ewahalmB@ "*d in Boeing Operations experience retention documents dealing with the following subjects: a) b) c) d) QUALITY ASSURANCE "Portable and Perishable Tools;" "Cryogenic Hardware Processing;" "Machine Shop Modernization;" and "Weld Fabrication of Large 22 19 Aluminum S-IC Booster Components. " In relation to the above mentioned improved mamifacturing techniques, Boeing/Michoud developed a presentation that points out how American industxy as a whole has benefited from the improved techniques developed. This presentation was made to the Subcommittee on NASA Oversight, Committee on Science and Astronautics, U, S, House of Representatives, and t o key personnel a%MSFC, A mechanized priority system was implemented in the mechanized procurement system during FY 1968. The receiving inspection daily status report now displays status and estimated completion dates for each priority item. A new "Work Plan" format for source surveillance and inspection has been completed. A source coordinator visited all field locations for the purpose of conducting an indoctrination course of the new plan. NASA representatives in the receiving inspection area audited the receival of gases during the month of Aunust 1961. Recommended actions were made to re&e that each receipt be chemically tested for all attributes of the procurement specification or have the vendor supply certified test data. Purchase orders were changed to require that certified test data be furnished with each receipt. A revbed system far planning inspections of government haisbed equipment has been put intoeffect. A detailed inspection record repIaced the previous "blanket" planning. A receiving inspection/source control work plan has been developed that provides for unified and coordinated inspection effort from release of purchase order until delivery of hardware to the production store. A review of the piece part inspection plans and failure rejection history was conducted during the fiscal year. The aim of this review was to reduce inspection when possible to do so without compromising the quality of the end product. The end result of this review was that inspection wa8 reduced �on certain parts, tncrcascd on some, and remained the s m e on others. d) Eddy current inspection for detecting surface cracks in steel spherical bearings and housings; The computerized Q&RA configuration accountability system was implemented during the redelivery of 5-IC-3 and was proven to be fully operatiannf d u r l a the rodellvery of tb 8-IC-4, This system i s a s e r i e s of interrelated comptiter programs that mechanize the configuration evaluation and accounting systems. I t will be implemented a t KSC for 5-16 -4 and on. e) Eddy current technique for detecting surface cracks in nonmetallic ablative coating; ft A system to provide visual and audible alarm at a remote location of the presence of a fuel leak; gj A system with an automatic tube feed that inspects lengths of aluminum tubing for rejectable surface defects with a visual and audible MT;P Q&TZA wnca reorgarixzed during FY 1988 to form a Qualitaf Engineering support section in addition to the existing test inspection and configuration accountability s e c t i o h , This reorganization provides overall quality program coverage for the MTF portion of the S-IC program. MTF Q&RA initiated the development of a computerized t'ab run system which provides an automatic recap system for all tests, a daily status report, and a work scheduling report. The tab run is a daily updated listing of all open, planned and unplanned, paper listed by location, milestone, and test event prerequisites. This system has resulted in an estimated savings of $84,000 annually at MTF darm; h) A new method of preparing mounts of titanium fasteners has been developed and implemented. The new method provides for mounting the fasteners in full section and then surface grinding, instead of splitting, on the cutoff machine. This provides a much superior specimen, with no cutting burns, which was very difficult to obtain previously; and i) A new test fixture was developed in the physical test laboratory to do torque and tensile tests on nut plates and other self-locking fasteners. The fixture reduces setup time and improves testing capabilities. . A facilities inspection plan was established by MTF Q&RA for inspection of preventive maintenance accomplished on all critical systems where &&RA is required to control functional configuration o r cleanliness level. Planning for 4 1 facilities work is being reviewed by Q&RA for quality requirements. The MTF &&RA organization also initiated a program of periodic inspection and preventive maintenance of government furnished property not formerly included in the preventive maintenance program. The development of nondestructive testing techniques is continuing. At the present time, the following techniques a r e under investigation and development: a) Crack detection in drilled holes - objective is to develop an ultrasonic technique and portable instrument to rapidly detect cracks in the sides of drilled holes with ultrasonic surface waves; b) Comparison of nondestructive test methods for weld inspection objective to compare the capabilities of visual, X-ray, eddy current, and ultrasonics to detect defects in welds using actual defects a s determined by destructive inspection as the standard; c) Soldering capability of printed circuit (PC) board objective is to develop an eddy current technique and instrument to determine the capabiuty of PC boards to produce an accept- TECWMMUES The development and documentation of nondestructive testing techniques continued during the reporting period. Techniques developed that further enhance our ability to verify the integrity of S-IC components are: a) Eddy current thickness measurement of nonmetallic coating; b) Ultrasonle mtrmuretment of metal Chicknesa from one side ; 6) 58 Eddy current techniques for identifying 3-nuts of different tempers; - - able @olderosmction; d) - Surface roughness measurements objective to develop an eddy current technique and portable instrument to rapidly measure surface roughness of machined surfaces; D5-1260 1-5 �- propagation dekction objective to p an ultrasonic technique (acoustic emission) to detect the propagation of cracks metals. Particularly directed toward longm stress corrosion crack generation in red structures; I - f) Weld penetratiqn monitoring objective to develop an infrared technique that measured the depth of weld penetration during welding process; g) Pene-trmt capabilities objecttve to compare the capabilities of selected penetrants to detect surface cracks in metal; and h) Ultrasonic hand scanner objective to evaluate the performance and capabilities of an ultrasonic system utilizing a portable hand scanner for spot weld inspection and other selected applications. - c) LABORATORY INSPECTION PROCEOURES The basic technical document for Factory Operatiomfiest Inspection, D5-11982, "Special Inspection Procedures" is continually being updated and expanded as necessary to reflect changes in hardware. The basic technique document for Factory Operations/'Test Inspection, D5-11997, "Quality Technical Instruction'', is also being updated and expanded as necessary to reflect the adoption of new techniques as they are developed. "Sampling Procedures for Fluids and Gases", Document D5-13666, is being rewritten to establish guidelines for all gas and fluid systems at MTF. This rewrite develops the criteria for systems sampling rather than components sampling and provides a single source for fluid cleanliness control. The end result will be the development of a composite Document D5-12855, "Cleaning, Testing and Handling of Oxygen, Fuel and Pneumatic Components", which will include the requirements and control methods to be applied to stage and support facility s y s t e m . Set up criteria for accepted certified vendor test data in lieu of in-house functional testing; b) Assure compliance to all safety standards during LOX compatibiZity testing of materials; and D5-126060-5 An additional portable magnetic particle tester ww reaeived and cer#fied for reaeivfnyr inspeation nondestructive testing; 6) Two new particle identification kits were received by the quality evaluation laboratories. These kits contain slides of identified contaminants that will aid in the identification of unknown contaminants found in clean environments or on cleaned parts; c) Two 23 by 70 inch "Mylar Flol' laminar flow benches were received and installed for contamination control and receiving inspection, These benches greatly increase the capabilities of both areas by providing a clean environment for inspecting larger clean parts and a second area for performing particulate contamination analysis; d) Receiving inspection acquired five additional 10-power lighted inspection glasses to aid in inspection of electrical circuits and other small electrical parts; e) The metallurgical laboratory received a set of eight electrical conductivity standards ranging from 1.0 percent to 101.2 percent, International Association of Copper Standards (IACS) to be used for the verification of heat treatment of alloy by eddy current method; f) Receiving inspection has received a Model PT-1033-8 Product-0-Ron for precision measurement of roundness and geometrical relationship. This instrument records measurements on recording discs to an accuracy of -+ 0.0000025"; and g) A portable vacuum tweezer system unit was received by the quality evaluation laboratories, This unit will enable personnel to collect and separate particles greater than .05" and, when wed with the Swinny Hypodermic Adapter, to Procedures have also been developed during the fiscal year tb: a) - TOOLS AND EQUIPMENT Following is a partial listing of tools and equipment that have been obtained and put into use during the reporting period: a) - Provide a method of obtaining and m a i n t a i n t ~ a record of corrective actions taken by suppliers on discrepant hardware. 59 �$ - collect particles lcss than ,OB" on 13mm dinnteter filters for conLmination and spectron acopic ,malysfs;i. a U A t l f V ASSURANCE ACTIVITIES QUALITY ENGlNEERlNG RNIWS - During the fiscnl year, quality engineering reviewed 75 engineering drawings, 330 engineering orders, 52 supplier acceptance test procedures, 330 supplier cleaninz tiocuments, and 110 company specifications for compli,ancc with the requirements of EN-I-V-S-IC68-13. Thcy nlso participated in six critical design INPLANT AUDITS SPECIAL AUDITS SUPPLIER AUDITS Figure 2-24 reviewe for supplier furnished bardware. QUACITY AUDITS Figure 2-24 denotes the quality program audits performed during F Y 1968. A total of 55 audits were made, sixteen of these were inplant, 13 were in special categories, and the remaining 26 were audits of Boeing suppliers. Audits performed resulted in a total of 467 discrepancies. The 26 audits of Boeing suppliers resulted in the identification of 54 system and hardware discrepancies. The not& ddlscrepanciee have been resolved, o r a r e in work at this time, �i SOURCE EVALUATION AND SURVEILLANCE The Michoud source control chart room has been expanded into an effective supplier performance and hardware problem analysis function. Supplier performance review charts are maintained that reflect both satisfactory and unsatisf acbry supplier performances, This technique provides source control management with the aides necessary to assess manpower requirements and placement, arrd permits a decrease in source control surveillance of suppliers with coqtinuoue satisfactory performance and a concmtration of carrective effort on those suppliers with current hardware or system deficiencies, Nonconformance data is analyzed, categorized, and displayed in the source control chart room in such a manner that impact problems and discrepancy trends a r e reedily recognized. This visibility provides a means of initiating timely corrective action of noted deficiencies, meaningful assessment of representative's performance, and effective product improvement. Product nonconformances are classified into one of four categories; critical hardware failures, noncritical hardware failures, critical hardware defects, and noncritical hardware defects, The number of nonconformances allowed to accumulate against a supplier before initiating positive remedial acffon depends upon the classification of the deficiemy as follows: Category f - Category II I Category ItI - Category IV - Critical Hardware Failure One Unit - Noncritical Hardware Failure Two Units Critical Hardware Defects Two Units - - Noncritical Hardware Defects Three Units - When supplier performance review charts indicate that a supplier is deficient in one o r more of the above categories, a product analysis report is generated. This report, which describes the deficiency in detail, is then forwarded to the cognizant source representative and a date by which the representative must ensure that the supplier has taken appro~ r i a t ecorrective and nonrecurrence actions is established. When analysis of a hardware deficiency indicates that previously delivered hardware and/or hardware currently in production c d d be affected by the same anomaly, the cugnfzmt representative fe - immediately notified by telephone. The problem is discussed and a decision made relative to withholding acceptance of hardware at the supplier's facility until the problem is resolved. When deficiencies in a product are considered to be of sufficient magnitude to withhold shipment, all affected inhouse materiel and quality control personnel are notified. This notification includes a description of the deficiency and the justification for withholding acceptance, Upon resolution of the reported deficiency, the representative is required to return the product analysis report, containing a complete description of the correotive action taken, to the Source Control offkre, The stated corrective actton is reviewed for adequacy and, if acceptable, retained by the supplier performance review group for future reference. Thh continual evaluation of supplier performance assures the delivery of high-quality products and provides the necessary management tools for maximum source control effectiveness. The practice of periodically performing in-depth hardware analyses and quality and process control systems reviews at selected supplier facilities has been formalized under Change Order MTCH-728, "Quality Maintenance Program. The purpose of the Quality Maintenance Program is to provide additional confidence that existing hardware will perform as intended and/or qualified, emphasizing critical hardware and hardware with no apparent problems. (A more complete description of the Quality Maintenance Program can be found on page 63 of this document.) A document has been released defining Quality Maintenance Program requirements, selected suppliers, and the tentative schedule for review. As now constituted, source control is responsible for constructing all review plans, scheduling and coordinating review team activities, providing team captains, and assuring that suppliers correct all noted deficiencies. Suppliers selected for review under the Quality Maintenance Program will be reviewed annually throughout the life of their contracts. The process control function has been realigned, Work plan surveillance is now being maintained at processors in the Southeastern area, The surveillance schedule provides for a minimum of two visits annually to each processor. All process survey and surveiIlance activity is now being handled through the Michoud source control office. RECEIVING INSPECTKIN The Xichoud receiving inspection group inspected and processed 32,539 lots during FY 1968, , I �QUALiN NALUATION LABORATORIES During 1988 mnjor investigations were conducted by the quality evaluation I,&oratories, Some of these investigations were: a) b) c) 62 An Pnvosttgntion of the possibility of corrosion of thc Saturn V fuel tank by microbial cont.unination found in RP-l fuel in February 1967 has k e n completed, No visual evidence of pitting o r any form of corrosion were noted on iridito test $-tripsof 2219 and 7075 dumfnurn aoys, Failure analysis of a cracked nut submitted to the quality cvduation laboratory by KSC d e t e r mined the failure to be due to s t r e s s corrosion crnektng. Thc basic material of the nut is 303 stainless steel. Intergranular corrosion was evident. Susccptibility to such a t h c k is attributed to excessive c ~ r b i d eprecipitate at the grnin boundaries. Carbon combines with chromium in the steel and may precipitate out a s chromium carbide at the grain boundaries during This and in s o doing i t depleted the chromium in the areas the and hence made the susceptible to intergranular attack, as chromium i s the main element for resistance to corrosion. A 300 s e r i e s alloy, such a s 304L o r 316L, with much lower carbon content that 308 has been discovered to be much l e s s susceptible to a t t s k , Periodic cracking when flaring 1/4 by .035 inch wall 606 1-T6 aluminum tubing has been a manufacturing problem for Some time. Nearly all such tubing has been procured from Alcoa to MIL-T7081 specification. Laboratory testing of this tubing has found it to meet the mechanical property and chemical requirements of the procurement specification. Flaring is done to MS33584 drawing, From considerable testing and examining done, regarding this problem, it is apparent that optimum conditions must exist in the tubing (including ideal chemical composition) before it can be consistently flared in the T6 condition. Very sIight discontinuities readily become crack initiators, Flaring tests on a sample of recently received similar tubing manufactured by Reynolds found it to flare acceptable. Comparison tests with Alcoa smples showed some difference in chemical composition, though both manufacturers were within specification requirements. Magnesium, f o r example, was 1.2 pex%f'cent irt the Reynolds tubing and 0.86 percent in Alcoa. Mechanical properties were determined to be essentially the same. General surface condition, though different (mottled on Reynolds and smooth on Alcoa) is not believed to be directly accountable for success or failure in flaring. Further testing is being done but at the present time it appears that chemical composition is a key factor in the resolution of the problem. PRODUCTION INSPECTION Ikicrementd in-process inspection co-hcidont d t h the build-up of the S-IC stage is continuing. The Quality and Reliability organization is providing support to Engineering for qualification t e s t i q , reliability testing and development testing. DUALITY ASSURANCE ACTIVITIES (MTF) Duality Engineering Review During F Y 1968, quality engineering reviewed 160 facility maintenance instructions, 39 acceptance test procedures, document D5-11789-100 test procedures, Bnd all inshplctionso The used were conformance to the end item test plan and IN-IY-S-1C-65- 13 requirements, and the incorporation of prerequisites, correct sequence, and safety requirements, Configuration Accountability The MTF GSE/MSE configuration definition was established by comparing the engineering "asdesigned" and the "as-built" configuration, This configuration assessment establishes the baseline necessary to support the development of modification programs. The "as-built1' configuration was used extensively in the review and development of the planned modifications to incorporate the engineering change proposals required to update the S-IC pneumatic console. S-IC-4 and -5 analysis data showed that Systems A Dynisco Pressure Transducers in use had a high failure rate. Investigation showed that, when the transducers were first received, they were discovered to have an unstable zero. The 150 transducers were returned to the vendor, where some of the potting was removed to allow the compensating network to be rebalanced. fnspection of the failed transducer also showed that the unsupported bridge compensating coil had failed due to metat fatigue. A substitate type of p r e s w r e traasducer was obtained and put in use, . D5-12601-5 �- --. [JRANCE A WIwa. WAC& AANCE The objcctive of the Product Performance Assurance function a t Michoud is to provide incrcwcd confidcnoe and assurance to both Boeing Management and NASA that activities critical to the mission o r program a r e ntified , planned, and accomplished. The organizarts directly to the Boeing Michoud Manager and im in discharG-ing his obligations for $uccessstags nigh*, ft is raspomible for monitoring. and assessing the adequacy of technical disciplines throughout design, production and test, and the integratfon of these disciplines to ensure total product integrity and st'age flight readiness, with supporting data. During FY 1968, Product Performance Assurance activlties were characterized by a continuation of a riskassessment approach and the promotion of techniques to strengthen disciplines to minimize o r eliminate identified risks. Particular emphasis was placed on greater focal-point administration of the three closely related disciplines of system safety, reliability, and quality assurance to provide for increased task selectivity within and among these three disciplines and the implcmenhtion of selected tasks in order of assurance effectiveness. STAGE FLIGHT READINESS ASSESSMENTS The final AS-501 formal flight readiness assessment of the S-IC-1 stage was conducted during the Apollo Program ~ i r e c t o r ' ; Flight Readiness Review on October 19, 1967. The MSFC Saturn V Program Manager's Pre-Flight Review (PMPFR) for the S-IC-2 stage portion of the AS-502 vehicle was held on January 16, 1968. This review was preceded by a similar review at the IHSFC Stage Manager's level on January 9, 1968. The PMPFR presentation consisted of an overall stage contractor and stage manager's assessment, plus a ~ystem-by-system review of the stage and its peculiar GSE. The final flight readiness assessment of the S-IC-2 stage was conducted during the Apollo Program Director's Flight Readiness Review on March 11, 1968. On April 4, 1968, the S-IC-2 stage was flown successfully. However, the second and third stages experienced some engine difficulties during the flight necessitating certain changes to the AS-502 mission profile. D5-12601-5 Both the AS-501 and AS-502 were unmanned flights. In the last quarter of FY 1968, NASA designated the AS-503 (s-IC-3 stage) as the first manned flight, Assessments of S-IC stage flight readiness ( a Product Assurance activity) a r e supported and validated through reviews by the Boeing Performance Board and Launch Readiness Board (see page 71, which consists of top management representatives from all Boeing/Saturn Programs. The Manager of Product Performance Assurance serves a s Secretary of the Performance Board. RISK APPRAISAL CYCLE Work continued during the reporting period on assuring the technical and performance integrity of the S-IC stage by strengthening the means fox timely identification of problem sources and dispositions, known a s the risk appraisal cycle, Figure 2-25 illustrates the sources of problems and screening processes used to arrive at whether there is any r i s k to the solution and if s o , is the r i s k acceptable for the next launch o r does further action have to be taken before the next launch. This activity is the cornerstone for arriving at stage flight readiness assessments a s discussed above. QUALITY MAINTENANCE ASSURANCE In February 1.967, ~oeing/Michoudinitiated a program to further assure the quality of vendor hardware, with primary emphasis on that hardware where failure could cause loss of crew or stage (reliability critical hardware) . During FY 1968, this activity was expanded under Change Order MICH-544 issued in July 1967 and Change Order MICH-723 issued in March 1968. The major areas constituting this program are: a) Michoud management team motivation visits to vendors to re-emphasize the significance of their hardware in successful Saturn V launches; b) In-depth audit of documentation associated with the engineering and procurement cycle for reliability critical hardware; c) Physical identification of hardware (and associated documentation) as reliability critical to highlight its unique stature in the function of the stage o r GSE ; 63 �SOURCES AND D l SPOSTION OF PROBLEMS RISK APPRAISAL CYCE 1 O P E N WORK L R B - ACTION BEFORE NEXT LAUNCH ACTION - - Z . POTCNTIAL TECHNICAL CONCLRN 1 + "TOP TEN" I ASSURANCE A R E A S O F CONCERN I I EVIEW A N D ASSESSMENT POlNfS AFTER P E R F O R M A N C E BOARD LRB Figure 2-25 S-tC Risk Appraisal Cycle d) Hardware review at vendors for such disciplines a s receiving inspection, processing methods, and quality control standards; e) Quality hardware analysis of vendor hardware consisting of both destructive and non-destructive testing; and f) Design confidence tests consisting of selected testing modes to augment and reinforce the qudification test program. Considerable progress was made during this fiscal year in accomplishing these objectives which are time phased for completion by the end of 1970. Results to date are contributing to increased confidence in total product integrity. Figure 2-26 is illustrative of the visibility given to this effort in the ~oefn&tXIZichoud Program Control Center. I #FAILURE A N D CORRECTIVE ACTION PROGRAM Continued emphasis was given to the area of hardware failures to further improve the disciplines involved in identifying, evaluating, tracking, and closing out such failures on a timely basis. A closed-loop system was established between Michoud and Boeing Atlantic Test C enter to provide for "real-time" visibility on failures. Also, a Failure Review and Assessment Board was created to review, assess, and dispose of W s e failures impacting the next launch. This board is composed of representatives from Engineering and Product Performance Assurance. SYSTEM OPERATION A N D S A F E N ASSURANCE An 5-IC Integrated Safety Program was established in October of 1967 under the administration of Product I �Figure 2-27 Figure 2-26 5-IC Organizational Safety Relationship Quality Maintenance Program PesEormfmaa Aaeurace, TMhfr pragrrun 18 respamiw to Boeing Corporate Policies and NASA requirements, The nwel aspect of t h i s program is that it combines and integrates the heretofore separate industrial and system safety into one safety plan and calls for organizational ancillary plans responsive to this master plan. Product Performance Assurance controls and maintains the master plan, approves the ancillary plans to ensure total safety integration and compatibility, chair the S-IC Safety Board consisting of organizational representatives and provides program direction as recorn mended by the Board. This arrangement provides for a single safety focal point for increased management control and improved visibility of safety performance versus assigned tasks. Figure 2-27 illustrates the organizational safety relationships including the composition of the S-fC Safety Board while Figure 2-28 depicts the controlling safety documentation for this integrated safety program. The S-IC Safety Board is chartered as a management working group to provide the means by which the combined attention of all organizations can be directed toward assuring safety excellence in the S-IC program. The Board meets on a regular basis and provides sui effective tool for the integration of organizational acb tivities relating to hazard tdentification m d control, Visibility on these activities is m-d in the Boeing/Michoud Program Control Center, Figure 2-28 Integrated Safety Program Controlling Documentation The line control safety effort is recognized as a continuing vital element in the master safety plan as is the Line Control Safety Council of line safety directors. This Council, as an adjunct to the S-IC Safety Board, continues to specifically assist line supervision assigned to production, test, and laboratory operations in carrying out their line control responsibilities. PRE-OPERATIONAL SAFETY REVIEW During F Y 1968, a pre-operational system safety review of the S-K-1 and -2 was held at KSC to provide for increersed safety assurance. This was carried �out aa part of a total system safety review of the AS561 aad 4 0 2 under Program Directives 44 and 44%. The purpose of these directives, as they relate to BoeIng Schedule I, is: a) - b, 44 - Provide correlation of the S-IC-1 configuration baseline and m a w e #at the 84G-1 launch vehicle, design, hardware, test specifications and criteria, software, and test procedures were consistent and compatible. '* - ments within Schedule I design'yetern 'lea and/or glosurance respansibiljtty are technfc* accurate, adequate, consistent, and cornn patible for AS-502 and -503, GSE, and KSC facilities. MSFC SYSTEM SAFETY NETWORK NEW T E CHN ()LOGY During 1968, a total of 54 New Technology disclosures were reported from Schedule I. One such item, which should have broad appeal, is a technique for makiw view graphs very quickly from expendable printsd matter, such a s magazines. The resulting transparancies mW be either in Or and white* , DELIVERABLE DATA Data submitted during PY 2868, in oompliance with the requirements of Contrwt NAS8-5608 (Schedules I & IA), are included in Append& D. Delivery of these items was in accordance with requirements wt forth in Document IN-I-VS-IC-67-10, "5-IC Progpaaa Deliverable Data. l1 TECHNICAL SUPPORT DATA . ��SUMMARY Facilities improvement activities at Michoitd during the fiscal year were concerned with fmprovcment of Boeiw/Alichoud production and fnbricntion capabilities. A s R pnpt of this program, flve numerically controlled machines nwre iwtalled and checked-out. Rearrnngoment and removal of outmoded machinery is also being accomplished. certain stores areas in the factory building, Boeing's activation tasks at the Miesissippi Test Facility were completed during F Y 1867. The formal letter acknowledging completion of the required tasks by The Boeing Company, was received from NASA on April 18, 1,968. �tion of certain areas nnci a reduction of space required for other functions. The installation of a new GOO0 psi CN2 gas header line In the high pressure test facility was completed during tho third quarter of FY 1968. Also, a request for additibnnl paving at the high pressure test facility was submitted and approved a s a NASA in-house responsibi1it-y. Thn l ~ c wpaving should be completed early in F Y 1969. SUPPORT AND GENERAL P U N T ROCKETDYNE FACILITIES MODIFICATIONS Modifications to the Rocketdyne area of the manufacturing builcting ware accomplished during March 1968. These modifications, which were requested by NASA, consisted of providing an office area and additional clean room capability, upgrading the helium supply, and completing other modifications which provided Rocketdyne with a complete working operation. Also in March 1968, at request, all thermal iwulation b f a n w s were transferred to RockeMyne for fication prior to shipment to KSC, Rocketdyne was also assigned 23,000 square feet of storage space on the south mezzanine to provide the space necessary to store and modify the insulation blankets. for additional equipment and the increasing need for better utilization of ow: existing equipment. It is estimated that there will be over 10,000 general-purpose type items that will be controlled and issued through the centralized store. During the pnst year, a rebuild shop, which allows BoeingJMichoud to rehabilitate machines that would otherwise require outside support, was established. OFFICE Significant progress toward reducing coets on the Saturn program was made during the fourth quarter of FY 1968 by consolidating office space. Plans are to deactivate, in early FY 1969, the entire southeast wing, first floor, of the Office and Engineering Building (No. 350). This will result in a considerable reduction in operations and maintenance costs over the ensuing years. TRAFFIC The Facilities organization, in conj~nctionwith the NASA-Michoud Traffic Safety Board, alleviated a large number of internal safety and traffic problems b.Y installing caution signs at dangerous intersections, adding additional speed limit signs and roadway markings, rerouting traffic and rearranging parking spaces in the parking lots. UTlLlZATlON FACILITIES FOR EQUIPMENT A utifization system for equipment was completed in November 1967 and it will be implemented a s soon as the switchover to third-generation computers is complete. This is an electronic system that monitors utilization of equipment items, such as machine tools and related production suppart equipment. Utilization is defined in terms of equipment run time, time under load, downtime and maintenance time, and is measured and recorded in actual hours on a real-time basis. The system is completely automatic from point of origin to actual recording, and can monitor up to 1000 pieces of equipment. All monitored equipment is connected to a central recording console via hardwire, and utilization of each equipment item is recorded on a machine processible format for computer input. MICHOUD FABRlCATlON PLANS AND ACTIVITIES " - GENERAL R A N T - The Facilities organization has implemented a centralized store concept that incorporates all general-purpose type test and production equipment. This plan was hplemented in view of the decreasing avairabilie of funds 72 STAGE STORAGE Early inFY 1968, it was recognized that there was not sufficient storage area for S-IC stages atMichoud. This inadequacy became a reality when revisions occurred in the transfer and transportation schedules of stages from Michoud to KSC At this time, Facilities planning prepared several proposals and a recommendation to solve this problem. The stage storage plan was presented, accepted, and approved byNASA. To implement the plan, it was necessary to relocate the specimen preparation area and major painting facility, and to double-deck certain stores areas within the plant. . Supplemental Agreement MICE-596 was received in August approving the storage plan. As a result , 14,000 square feet of double-decking was confitructed for storage space (8000 square feet in the factory building and 6000 square feet in the vehicle ' component supply building). Positions 1 and 3 were completed on schedule and supported the revised delivery schedule. Position 2 became available inApril 1968, Alf effort connected withthis project was completed in June 1968, when the floor and ramp repairs were completed. D5-12601-5 �AUGMENTATION, MODERNIZATION, REHAEffLITATIOM A N D REBUILD PROGRAM Approved F Y f 967 funds (Contract NAS8-5606(F)) for modification, replacement, and rehabifitation amounted to $1,895,195, Thesc funds have either been oomc rnitted o r a r e in the processof beingcommitted. During F Y 1968 5930,000 worth of funds were approved f o r Contract NASB-5606(F). b, ' i ' MISSISSIPPI TEST FACILITY P a s t annual progress reports have concentrated on the facilitfes activation &%sirsat MTF During FY 1967, The Boeing Company's facilities activation tasks a t MTF were completed. The letter certifying cornpletion of activation at MTF was submitted to the NAW/MTF Contracts representative for concurpence on January 24, 1968. The letter of completion, recognizing concurrence on the part of The Boeing Company, was reccived by Boeing on April 18, 1968. . S-1C-5 STATIC FlRtNG ACTIVITY The S-IC-5 was installed in the S-IC test stand at MTF on June 29, 1967 (Figure 3-2). Stage electrical connections were completed on July 12, and on July 13, 1967, power was applied. Propellant load tests were eompleted by August 9, 1967, and the stage was successfully static fired for 125.096 seconds a t 6: 14 p.m. , August 25, 1967 (Figure 3-31, The S-IC-5 stage was removed from the static test stand on September If, 1967 (Figure 3-41, and returned to Michoud at approximately noon the following day. Figure 3-4 S-IC-5 Being PROBLEMS ENCOUNTERED AND RESOLVED DURING S' S-IC-5 STATIC FIRING ACTIVITY Figure. 3-2 D5-12601-6 S-IC-5 in Test Stand Thrust Vector Control (TVC) system checkout began July 21, 1967. During checkout, two Hydraulic Research servoactuators were found to be defective. They were returned to the vendor for failure analysis and replaced with serviceable items. TVC system oheelrout was completed August 4, 1967. 73 �XPP-1 tanMag commenced J d y 25, 1567, After tanlciw ha& reached ?O wrcent fill level a shtdrlown ww called due ttz Chc collapse of a fucI emergency drain duct (Ffntra 3-51. An hZTF investigutinb. committee was In~media'delyfosmezl to determine the cause of thLq ini~fcfonk. Spocblad test rbcju$remon~WOFQ orntlhed ts dewmine the recirculation flow m d pressuse charactcristics of the facility fueling system, These tests WCP'C co~niJuctedan J u l y ZF, 1967, and sufficient negative preusttrss were encountered within tire system to have a a u ~ s dthe duet t o coifapse (a ctoscriptiou of the cmses ol Chis oollgf,'se w e @apage 45), dHI a l g a lp~owlXsmt t e s b were 8usprenete-d pending a review and evaluation by the Branch investigation t e r n wNeh was held July 27, XOG7, The facility fael emergency drain duct sysQ S ~ ~ k &$ubst"que~tly q modified a d rehrued to operatSoaal eodi~w;llsatiotl, F i n d Branch investigation t e r n recommenrfations for revising LOX loadp r ~ c d u f e swere complied with prior lo pyaload bstts, which were completed on 4rernreb a re=- ,high pressurr?a, therefore , on August 5 , 1967, i t was removed and replaced. During preparation for the S-IC-5 static firing engine servoactuators were changed out f.4 times because of le&ge, axereme limit cycling, out of specification ia the lock-off-null position, anci piston rod seat leaks out of tolercmce, ". Duriw static firing of thc S-1C-5, a Z-inch piece of tha tarbinn? h i s t tomperatuse maasr~iwtthsrm~colngle crgehd md brake, off, Eta~XreMyaefowd the pigcs in one of the turbine manifold nozzles of engine position 102. The piece trm removed and the exl@ne returned to o p e r a t i o d corrf~wration,a pressure leak check retest was aaQsfactorily performed oa September 8 , 1967, PLtST-STATIC FIRING ACTiWifY Qn A~tgust31, 1967, a stand-up presentsttion ~vmgiven by B w u g to stuumarize the static firing five-day "Qdck Lmk Repot%," This presenbtiaa revealed that '94 perceat of the System "Ar7measurements recorded during static firing of the S-XC-5 \%re good. A lf Certificates of A ccamplishen~tfor completion of the S-XC-5 acceptance test procedures were rebased by September 26, 1967, 8-iC-B STATIC FIRtsNB PREPARATBOM The S-IC-6 stage was shipped from Mic2loud and mrived at MTF on March 1, 1968. The stage w s then placed in the tata at if test ~ h ondN w e h 4, 1968. Y A req~xisement11y fada&% to rerun s h hfSE a~domatic checkoat procedmes , psiur ~ t a g epower-on, delayed power-on from M u c h 25, 1968 to April 4, 1968. Three of the six MSE ~utomaticcheckout procedwes that NASA reqEEir@dto be rerml cont.talaed errors and were returned to Michoud for correction, Initid power-oa was sxaeeessfully accomplished on April 4 , 1968, a d heat shield installation was ssu@@essfally completed 0x1April 5. i Figure 3-5 Calfapsed S-1C-5 FweO Emergency Drain Duct During the imtallation of a heavy manudl efig2oe aeluator on J d y 35, 1967, tkte No. 1 fuel && pressme duct on e e e 1Q4 m go~ged. Af er the gauge was polished, in accordance with a RockeMyn~disposition, Uzo NoU 1 &el high pressure riuct waas, b e &in to suppor-f; 74 On Agrfl23, 31968, %-IC-Ci s t d i e firingactivity was . suspended n$th the exception of 8utborized modifications, This w m cFo~.loso tllczlt several m d f i c a t i o ~ ~ resulting s from AS-502 Bight iuadysis could b incoa.psrated rtnd teslhd on the 6-IC-6 prior to the decisim to ixlelude them on the 6-EC-3; the prhcipipali changes to be tested a r e V 0 6 8 s@pressioa systems (set? pwe 37). A review of cbmges affecting t h 8-16-6 ~ was conducted with tXne purpose sf "raUing back? dl chmp;es practicable for aecompl1Isbment prior to 8 Inter s&Bo f i r i w sched- ule, 135-12601~-5 i i . , �fncorporatlon of tflc required POGO suppression sys- , tern on tile S-IC-G began on June 14, 196s. Stage power-on was trccon~plishedon June 26, axid static firing of the S-IC-li is scheduled for Auwst 6, 1968, S-IC-D FUEL TANK DRAIN TESTS (ANTI-VORTEX) - dl ;-crrit?xi~gcund'ition was observed during Ij8tl-j segment fuel tank drain tests at Michoud. A vortex formation in the fuel Lank during flight could cause gas ingestfon at tile engine fuel punlp inlets, and could result in engine explosion. Because of a need for Eurther testing, the S-IC-D was installed in the MTF static test stand (Figwe 3-6) and modiffed s o that water drain tests could be conducted to determine i f a vortexing condition existed in the stage fuel tank. Modifications included removal of tlie S-iC-D engine simulators, and Figure 3-7 Plexigiass ~ u c t sInstalled on S-IC-D ing, it was decided to terminate drain tests, and replace S-XC fuel tank anti-vortex assemblies with a~qsembXiesof the same design as those used on S-XC-1 and -2. S-IC PNEUMATiC CONSOLE Figure 3-6 instaliation of S-IC-D in Test Stand installation of necessary monitoring equipment including ten plexigl,ws ducts which were installed on the fuel ducts to allow high-speed photography of bubble ingestion patterns f see Figure 3-7), ~ea;in(: began on December 18, 1967 and was completed on Jaztliazy 27, 1968. During that period of time, a total of 20 tests were cortducted on four different antivortex bdtlea. The basic test consisted of filling the fuel tnnk ~4thwater to the 40 percent level and then cameras located inside record bubble fctrmatio Test data reduction was comple Work continued throughotd FY 1968 to revise the pneumatic console vent and relief circuitry. The original vent and relief circuitry was not designed for a "wide open" reedator failure. If this type of failure was to occux, it would came an over-pressure condition to exist i n the do\riastream piping and could abort a launch. For various reasons, but principally because of the unavailability of parts, the work of modifying the console was sporadic, workarounds were implemented so console modifications would not affect S-IC -6 power-on. GROUND EQUIPMENT TEST SET Because the manual Ground Equipment Test Set (GETS) was designed as a continuity tester with no automatic stage simulation capability, stage sequence tests could not be verified without an S-IC stage. To eliminate the use of an S-XC strage as a test fixture for verifying ground support equipment. operation and for developing t programs, the manual GETS to a super or automatic GETS ion. This modification was begun on Octomd completed November 17, 1967. ckout was completed Novembor 27,1967. 75 �in static firing, was incorporated. The pipe assembly, necessary for the rework activity, was built at Michoud and delivered to M T F on April 26, 1968. The change was functionally complete on May 13, 1968, GSUMSE t ? i t 1 I1 i i I I /: Early in J~inuary1968, General Electric QuLzlity znd HeUabiliW Assurance Engineering reported that comblning Stngefok and Cyrolok tube fittings could cause "a potential hazard to safety, tutd a detriment t;o operatlon," General Electric hnd been issuing the tube fittfngs on tho assumption that the two varieties were interchmgeable in all combinations, A Boeing committee 'K'W appointed to investigate the possibility of any anomalies in the Ground Support Ecluipmenthfanufacturt?rsQuppo~tEquipment (GSE/NISE) installations. An bvcsltgaU.an wa9 conducted as a result of Uloir findings m1d it was determined that no intermiuing of S~tageloMGyroloktube fitting components existed on the S-IC static test stand, cw stated in the oommitteelrr rcport of M u c h 1968. Work was started iti l a b February of 1968 to provide a capability for remote pressurization and venting of the GOX ductsystems, The test fLuture, used to marmally vent the COX ducting system during confidence and leak tenting, presented a s d e t y hazard during confidcnce testting and therefore did not meot personnel safety requirements j f I . The tost fixture was sent to Michoud for re~vurkon February 26, 1968, and a workaround version, borrowed from Michoud, was modified for use a t M T F during the time tile reworked test fixture was at Michoud. a i\iaGficatioxt of the hydraulic terminal equipment to eliminate l e m e and/or functional failure of the pneumrrticdy operated ball valves and ~ s o c f a t e dp n e u m t u ic and electrical controls, which would cause a dolay Work to add rQmoh vQntfW$CWabfliW to gmeow nitrogen (GN2) control pressme s p s b m s was started on March 18, 1968. This ~ v a sdone to eliminate a potellaal Wrsonnel safety hazard by providing remote venting. of trapped high pressure GN2, and to retain sufficient GN2 pressure to allow prevalve closure during flight to ensure mission cornplotion. The change was originally committed to be i n s t d e d at Michoud prior to stage shipment to M T F but, because of the late delivery 6f hardware, the change was made at M T F . , The change to add the above mentioned remote venting to the ON2 control pressure system made it necessary to remove the stage mounted prevalve accumulator bottles from stages S-IC-6 and on. Certain tests, performed to v e r i b operation without the accumulators, were sdisfactorilly completed and the change was begun at M T F on Mwch 18, 1968. The tubing required to add remote venting and to remove the accumulator bottles was sent to Michoud for fabrication, testing, and cleaning. Installation and functional checkout wm conrploted on March 26, 1968, MTF DQCUMEWTAP1ON Boef.q/WI.Tf" document statup, for FY 1968 is indicated Jn Appendix G, r * Q 76 D5-12601-5 ��DOCUMENTATION $UPPORT "S-IC LOGISTICS LAUNCH SUPPORT PLAN," DS-13705 This document describes the actions necessary to ass u r e complete and timely Schedule 1 logistics support for the S-IC launch, and has been updated to incorporntc changes resulting from the S-IC-1 launch. However, there knvc been no signlficttnt changes in the manner o r scope of logistics support. SPARE PARTS STATUS SUMMARY The Stock Status and Consumption Report, DRD MFhas been deleted by con506B of IE-I-VS-IC-65-10, tract change and replaced by a Spare Parts Status Summary, DRD LS-078 of EN-I-VS-IC-67-10, for each stage. Reporting for the summary of each stage is to begin thirty days prior to the on-dock KSC date, and will reflect logistics1 support position for that stage, TECHNICAL SUPPORT DATA Publication of S-IC stage and GSE technical manuals continued on o r ahead of schedule throughout FY 1968. During this period a complete revision on the S-IC-2 Stage Maintenance and Stage Flight Measurement Manuals was published. Also, a total of fifteen GSE technical manuals were revised. "LOGISTICS INFORMATION REPORTING SYSTEM," 05-13759 The implementation of third-generation computing equipment necessitated reprogramking the logistics reporting system. A study was conducted to devise a system which would utilize the potentials of advaiced computing equipment and better satisy Iogistics' needs. The resulting system has been documented in D5-13759, "Logistics Information Reporting system, I' and is scheduled to be implemented during October 1968, CENTRALIZED INVENTORY CONTROL SYSTEM q Implementation of a centralized inventory control system was postponed because of a delay in the avail- ability of video displays Cathode Ray Tube (CRT) units. When available, these units will allow direct communication with the file in a third-generation online computer, and will function a s an integral part of the logistics program. SPARES SUPPORT Three "sparesv hardware stores were supported during FY 1968. The Michoud store was used as a central store for test site provisioning and a s a site support store for post-manufacturing checkout and poststatic test checkout operations at Michsud. Stock at the MTF store was built up and maintained in support of S-IC-5 and -6 static tests. A limited number of parts from ,the MTF stores were diverted to KSC for backup support of launch critical applications, however, a full inventory level at MTF was maintained. The S-IC-1 and -2 launches were successfully supported with no delays caused by spares shortages. At the end of the fiscal year, stock levels were satisfactory at all sites. The task of refining and operating an effectiveBoeing/ vendor repair program for failed repairable components is being reviewed. This review has important implications for future spares support due to kxtensions in the program performance period. PERSONNEL SUPPORT To assist BATC in the spares liaison effort to support the S-IC-2 test and launch, Logistics Engineering placed two additional spares maintenance representatives at KSC prior to the beginning of the Countdown Demonstration Test. The loan of these two additional liaison personnel provided round-the-clock liaison between Michoud and KSC , resulting in rapid resolution of any spares problems that might have impacted test and launch operations. The personnel on loan returned to Michoud immediately after the launch. SPARES FOR GOVERNMENT FURNISHED EQUIPMENT A logistics problem was encountered with the GFE provided to MTF by MSFC and operated by Boeing. This problem is associated with lack of design definition and resulted in our inability to obtain formal design and drawilig corrective action on discrepancies noted during spares provisioning and procurement activities. However, in spite of such problems, the spares support position for GFE has continually improved during this reporting period, . ��LAUNCH OPERATIONS There has been an on residence Test Conductor at BATC from s-fC Systems Tests T e s t Engineering and Operatiom M ichaud to support AS-$03 processing. - depth review and audit of all change incorporation, rework and retest activiQ involving the S-IC-3 from the end of Post-Manufacturing Checkout (Simulated Static Firing, 8-24-66) through May 1968. This review was directed by NASA a s a result of the AS-502 flight failures. The initial Branch report was submitted to the customer on June 5 , 1968. ��APPENDIX A APPENDIX C CONTRACT MODIFICATIONS NEGOTIATIONS COMPLETED The number of contract modifications received during the period July 1, 1967 through J w 30, 1988, i e as follows: The number of negotiations completed with NASA during the period JuIy 1, 1987 through June 30, 1968, is as follows: Contract NAS8-5606{F) Ctantrnat NAS8-5608 Csntraat NAS8-1BIM -- 6 251 Cohtraet NAS8-5608 Gontrwt NA68-29844 1 -- 93* 1 *Totaling approximately $8,155,063 APPENDIX B APPENDIX D PROPOSALS SUBMITTED DELIVERABLE DATA SUBMITTED The umber of firm cost proposals aubrafmd ta N A a dwiq Mi@ period Ju& 1, $867 Ju\ht $08 28813, le The number of items of deliverable data submlmd $Q &A% duardxag~the priad July 1, 1867 Ukraugh 3we 90, lQ4i8, i a as foIlows: as follows: �APPENDIX E ENGlNEERtNG CHANGE DOCUMENTATtON COMPLETED DURING FISCAL YEAR 1968 CHANGE NO* DESCRIPTION EFFECTIVrl'IES STAGE GSE 0247 Provide filter networks to reduce noise susceptibility and realign LOX and fuel loading electronics assemblies 0248 Replace orifice irk fuel pre;prasrsuriaation msdufe of the S-EC pneumatic cansole MTF f MILA 1, 2, 3 MAB 0249 Redesign aft umbilical # 1, $2, and #3 ball valve actuator arm MILA 1,2, 3 0250 R p o v e ground umbilical fluid couplings from spare locations in S-IC umbilical equipment 3-15 0261 Replace helium shutoff valve with a check valve 1-2 0264 Replace roller stops on LOX interconnect support bracket installation 1-15 0265 Replace roller cams on LOX interconnect support brackets 1-3 0266 Provide capability to vent downstream of helium bottle fill isolation valve 0267 Rework circuitry of the DC-DC converter and DC power isolator 0269 Provide separate vent lines for the presertation module of the forward umbilical service unit MILA 1, 2, 3 0270 S-IC engine alignment check MTF 1 0273 Provide identification of S-IC stages by numbers 3-15 0275 Provide manllal ground control of stage prevalves at K5C 1 MILA 1, 2, 3 0276 Provide power-off turbopump seal purge capability 1-15 MILA 1, 2, 3 0279 Prevent corrosion of spherical rod-end bearing used throughout the S-IC stage structure 2-15 provide electrical bonding of retrorocket and manifold 1-15 9 E 1-15 MILA 1, 2, 3 MSE 1, 2 MAB MTO 1 MAB MILA 1, 2, 3 1-15 c e 0280 ' CDF 98 D5-12602-5 �CHANCE NO. DESCRIPTION E FFECTIvlPTfES STAGE OSE 0285 Incorporate improved lockwire installation procedure on fluid power system duct insulation installation 3-15 0286 Revise visual fnstrumentation camera port squib cable assembly 2, 3 0288 Add remote venting caa>abiIlty of GNZ control prsssurtzation sysbm 2-15 MTF 2 MSE 1, 2 MAB 0289 Remove stage mounted prevalve accumulator bottles from the S-IC vehicle 6-l6 MAB 0290 Modify the fuel tank prepressurizsation module of the S-IC pneumatic console MTO 1 MILA 1, 2, 3 MAB 0291 Revise engine cocoon thermal conditioning controls and thermocouple cable acceptance test requirements 0295 Revise S-IC Level I electromagnetic compatibility test requirements 0298 Add inlet filter to the forward umbilical service unit 0299 Provide sealing of stage structure to prevent equipment damage from rain w a b r 1-15 Provide redundant electrical power circuit for fuel pressurization system 3-15 0302 Replace 50M04050-1 Hydraulic Research servoactuator with 60B84500-1 MOOG servoactuator 1 0303 Modify the S-IC pneumatic console LOX/fuel prepressurization modules 0305 Rework 60B84500-3 Hydraulic Research servoactuator 3-15 0306 Rework prefiltration valve subassembly on MOOG servoactuator 60B84500-1 3-15 0309 Relocate the positive pressure line on the LOX and fuel tank upper m e a d s s 4-15 0300 D5- 12601-5 * I I MILA 1, 2, 3 MAB 7-15 MILA 1, 2, 3 MILA 1, 2, 3 MTO 1 MA3 99 �G&MNGENO. EFFECTNITIES GSE 8TAGE EfESCItFPTION Provide separate mounting of three pilot relief v d v e subassemblies in the S-IC pneumatic console 0312 MTF 1 MILA 1, 2, 3 MAB 0313 Revise electrical surge suppression circuits in the S-IC pneumatic console 0315 Delete non-flight hardware from flight documentation 2-15 0316 Rework the Hydraulic Research servoactuator 50&104050-1 removed from S-IC-1 and use them for S-IC-2 2 0318 Add LOX pressure sewing line to the intertank umbilical reconnect assembly 0320 Revise fairing turn buckle attachment fitting material to 7075-T73 1-15 032 1 Provide Parker LOX vent and relief valve as standby for Whittaker LOX vent and relief valve I 0322 Provide explosion proof enclosure for prevalve ground accumulator pressure spheres Sr MTF 2 MILA 1, 2 , 3 MAB MILA lr2, 3 MTF 2 MILA 1, 2, 3 0323 Revise S-IC propellant dispersion system installation 2-15 0324 Revise test requirements and procedures for ordnance safe and arm device 2-15 t MILA 1, 2, 3 0328 Rework the intertank umbilical locking mechanism 0329 Reroute cable installation on fins B and D 2-3 0330 Substitute amplifier used for ten mandatory prelaunch red line temperature measurements 3-15 10332 Revise the S-IC stage thrust structure hazardous gas detection system to provide sampling orifice in each quadrant 3-15 0335 Remove, retest and re-identify dl 65B23280 check valves MSE 1, 2 MTF 1 MILA 1, 2, 3 Q 100 OM4 Modify the fairing heat shield access panels 3-15 0345 Add weather protection covers to base air scoops 2-15 I%-1260 1-5 �DESCRIPTION EFFECTlVITIES STAGE GSE iminate 17-7 P H mechanicd feed back rings in trydrauh Research S-IC servo- 3-15 im engine fairing skin to prevent injury 3-15 odify servoactuator jack pin assembly MSE 1, 2 MTF 1 WILA evise materid of stage anti-friction plates 3-15 Provide additional vents for the servoactuator and Boeing supplied engine thermal 2-15 dify servoactuator boot fitting installation to lace fasteners with through bolts 3-15 Change S-IC documentation to comply with KSC pull test requirements 2, 3 Provide positive moisture sealing of electrical vities for the 60B49002 helium pressurization d emergency dump valves 2-15 ncorporate improved position switches in the 2-15 LOX tank vent and relief vqlve (60B51002f Instdlation of the ordnance bracket assembly on the LOX and fuel tanks 2-4 Protect electrical cables a entry {forward and aR) to stage from electricd tunnel 2-15 Revise S-IC propellant dispersion system installation kit Provide uninterrupted power (+28 VDC) to LOX and fuel loading electronics KSC Genl 3-15 Modify S-IC interta.uk umbilical lock mechanism MILA 1, 2, 3. 0372 Modify the S 4 C pneumatic console helium primary regulation circuit MAB MTF 1 MILA 1,2, 3 0374 Revise the main sed in the LOX fill and drain valve 335- 4260 1-5 3-15 �CHANGE NO. 102 E FFECTWITIES STAGE GSE DESCRIFTION MLA 1 0377 Modify the S-IC storage racks to provide protection during launch 0379 Replace vent seals on all Aireseareh prevalves md emergency drain valves 5-15 0382 Eliminate H e flow overlap of the stage and ground fuel tank pressurization system 2-15 0888 Modify filter m W o I d delta pressure 9-31s 0396 Block debris valvejs in S-IC intertank reconnect assembly LOX fill and drain lines in the open position 0401 Provide locking and position indicating mechanism for S-fC pneumatic console and forward umbilical service unit MSE 1, 2 MILA 1 MTF 1 MILA 1, 2, 8 MA33 0406 Modify TV objective lens housing assembly 2,3 0411 Provide drain for servoactuator rod seal leakage 2-15 0414 Replace bolts in fairing heat shield access panel 3-15 0415 Replace 50M04049 MOOG servoactuator with 60B84500 MOOG servoactuator 2 0419 Provide new latch on the S-IC intertank umbilical reconnect assembly MILA 1, 2, 3 0848 R1 Replace pressure gage in forward umbilical service unit LUT #1, #2, #3 0866 R1 Modify heater blanket assemblies 1-3 0867 R1 Modify base heat shield installation 1-15 0868 R1 Modify connector hex nut 3-5 0870 R1 Modify base heat shield support angle installation 1-4 0871 R1 Correct bolt lengths on lower fairings 3-15 0873 R1 Modify support installation to allow installation of the recoverable camera 2, 3 0874 R1 Correct bolt length on thrust structure baee air scoop installation 1-15 0875 R1 Provide pilot relay for heater power contactor in 5-IC pneumatic console MILA 1, 2, 3 MTF 1 t D5-1260 1-5 �E FFECTlVrl'IES CHANGE NO, DESCRUPTfON STAGE 0876 R l Modify ground cables in TV camera system 2, 3 0877 R 1 Modify retrorocket initiation system 1-15 0879 Bl - MILA 1 Modify tube assembly in the pneumatic console 0880 R 1 Eliminate an out-of-tolerance condition in the LOX leakmeter measurement F45-118 1-5 0883 R 1 Correct bolt length callout on servoactuator boot installation 1-15 0884 R 1 Modify length of cable assembly 115W305 1-5 0885 R 1 LOX f i l l and drain valves (3-239, B240) MILA 1,2, 3 MAB MTF 1 control valves reversed cables 0887 R1 Calorimeter purge line clamp 0889 R 1 M9dfa7S-IC inbrtank umWUed to delay GSE 2-5 XMXu olotswe of detJsir%r vRIvr3 0891 R 1 Heat shield panel installation 2, 3 0892 R l Electrical installation forward skirt 2, 3 0893 Rl Eliminate leakage in LOX pressure sensing line MILA 1, 2, 3 0896 R1 Housing assembly aft 1 and 2 MILA 1, 2, 3 0897 R1 Rebonding of anti-friction plates 2 0903 R 1 Engine fairing blanket assembly 2-15 0904 R 1 Cable and instrumentation installation units 101 and 102 2-4 0906 R 1 Measurement installation fin B 2, 3 0907 R 1 Propellant dispersion system installation and retrorocket initiation system 2-15 0908 R1 Change bolt callout 2-15 0913 R 1 Rase heat shield bracket misalignment 3-15 1214 G Increase accuracy of GOX flow control valve pilot pressure measurement I I MSE 1, 2 ��ENGINEERING CHANGE DOCUMENTATION I N n l A T E D DURING FISCAL YEAR 1968 CHANCE NO. e DESCRIPTION E FFECTTVPTIES STAGE GSE Reduce the fuel and LOX tank standby pressure output in the forward umbilical service unit MILA 1, 2, 3 0231 Cancelled Provide 6-IC engine hydraulic sysbm pressurization for stage shipment and storage MILA 1, 2, 3 MTO 1 0242 Modify S-IC pneumatic console to provide pressure calibratian source in mobile launcher room MILA 1,2, 3 'NIAB 0247 Provide filter networks to reduce noise susceptibility and realign LOX and fuel loading electronics assemblies 0248 Replace orifice in fuel prepressurization module of the S-IC pneumatic console MTF 1 MILA 1, 2, 3 MAB 0249 Redesign aft umbilical #1, #2, and # 3 ball valve actuator arm MILA 1, 2, 3 0250 Remove ground umbilical fluid couplings from spare locations in S-IC umbilical equipment 3-15 0251 Modify the length of the telemetry antenna feed cables 3-15 0260 * Cancelled Replace angular rate gyros for measurements R4-120, R5-120 and R6-X20 2-15 0261 Replace helium shutoff valve with a check valve 1-2 0263 * Cancelled Provide venting for stage access equipment storage racks 0264 Replace roller stops on LOX interconnect support bracket installtion 1-15 0265 Replace roller cams on LOX support brackets 1-3 0266 Provide capaljility to vent downstream of helium bottle fill isolation valve * 1-15 MILA 1, 2, 3 MSE 1, 2 I* MAB MILA 1, 2, 3 MTO 1 MAB MILA 1, 2, 3 0267 D5-1260 1-5 Rework circuitry of the DC-DC converter and W: power isdatas 1-15 105 �DESCRIPTION CILZNGE NO, EFFECTrnfES STAGE CSE 0269 Provide separate vent lines for the preservatioa module of the fortvard umbilical service unit MILA 1, 2 , 3 0271) 9-IC en&&@alignment check MTF 1 0272 Provide S-IC forward skirt access equipment for access to S-II engfnes 2-15 0273 Provide identification of S-IC stages by numbers 3-15 0274 * Cancelled Remove umbilical fluid coupling from spare location on S-IC umbilical equipment 2-15 MSE 1 , 2 MTF m u 1,2, 3 0275 Provide manual ground control of stage prevalves at KSC 1 MILA 1, 2 , 3 0276 Provide power-off turbopump seal purge capability 1-15 0279 Prevent corrosion of spherical rod-end bearing used throughout the S-IC stage structure 2-15 0280 Provide electrical bonding of retrorocket and CDF manifold 1-15 0285 Incorporate improved lockwire installation procedurw on fluid power system duct insulation installation 3-15 0286 Revise visual instrumentation camera port squib cable assembly 2, 3 0287 Modify Marotta solenoid valves (65B23278) 0288 Ad&remote venting capability of GN2 control pressurization system 2-15 MTF 2 MSE 1, 2 MAB 0289 Remove stage mounted prevalve accumulator bottles from the S-IC vehicle 6-15 MAB 0290 Modify the fuel tank prepressurization module of the S-IC pneumatic console MTO 1 MILA 1, 2 , 3 MA3 '0291 Revise engine cocoon thermal conditioning controls and thermocouple cable acceptance test requirements MILA 1, 2 , 3, MAB i 106 MTF 1 MILA 1, 2, 3 MSE 1, 2 MAB D5- 1260 1-5 �CHANGE NO. E FFECTWITIES STAGE CSE DESCRIPTION 0292 Provide backup engine pump seal purge systems 0293 LOX engine cutoff sensor solar cell redesign 0294 * Add a mechanical relicf valve in the helium bottle gas storage system 3,4 0295 Revise S-IC Level I electromagnetic compatibility test requirements 7-15 0296 Add instrumentation provisions to the S-IC pneumatic console forward umbilical service unit and S-IC umbilicals 0297 Provide digital range safety command system antenna shields Q298 Add idet filter ta the fornard umbiliod service C aneelled MTF 1 NlfltA 1, 2, 8 PAAB 2-15 NIXLA lt2,3 uazlt Provide sealing of stage structure to prevent equipment damage from rain water 1-15 Provide redundant electrical power circuit for fuel pi-essurization system 3-15 0301 * Cancelled Incorporation of second source LOX vent and relief valve 6-15 0302 Replace 50M04050-1Hydraulic Research servoactuator with 60B84500-1 MOOG servoactuator 1 0299 0300 . r Modify the S-IC pneumatic console LOX/fuel prepressurization modules 0305 Rework 60B84500-3 Hydraulic Research servoactuator 3-15 0306 Rework prefiltration valve subassembly on MOOG servoactuator 60B84500-1 3-15 0309 Relocate the positive pressure line on the LOX and fuel tank upper bulkheads * . MfLA 1, 2, 3 MTO 1 MAB 0303 . 4-15 0310 C ancelied Add umbilical interface measurements to vehicle IP&C list 1-15 0311 Provide redundant circuitry and power in the stage separatidn system 3-15 MTF 1 MILA 1, 2, 3 MSE 1, 2 �EFFECTNITIES CHANGE NO, 0312 DESCRIPTION STAGE' Provide separate mounting of three pilot relief valve subassemblies in S-IC pneumatic consale GSE MTF 1 MILA 1 . 2 , 3 MAB - 0313 Revise electrical surge suppression circuits in the S-IC pneumatic console MTF 2 MILA 1, 2, 3 MAB 0314 Add calibration valve to pressure switch sensing line MILA 1, 2 , 3 0316 Delete non-flight hardware from flight documentation 2-15 0316 Rework the Hydraulic Research servoactuator 5011104050-1 removed from 8-IC-1 and use them for S-IC -2 2 0317 * Cancelled Combustion chamber pressure measurement telemetry channel change 5-15 0319 Add LOX pressure sensing line to the intertank MILA 1, 2, 3 Provide redundant 28 VDC monitoring power circuitry in the S-IC pneumatic console MTF 1 MILA 1, 2, 3 MAB 0320 0321 Revise fairing turn buckle attachment fitting material to 7075-T73 1-15 Provide Parker LOX vent and relief valve as 1 ' standby for Whittaker LOX vent and relief valve 0322 Provide explosion proof enclosure for prevalve ground accumulator pressure spheres MTF 2 MILA 1, 2 , 3 Revise S-IC propellant dispersion system installation 0324 Revise test requirements and procedures for ordnance safe and arm device 2-15 0325 Provide a redundant method for initiating center engine cutoff under LOX depletion condition 2-15 0320 Cancelled Delete BMS8-38 sta-foam from S-IC electrical distributors 3-15 0327 Modify the LOX vent and relief valve configuratiw by removing the actuator gear clutch springs 9d15 0 * MTO 1 MILA 1, 2 , 3 MSE 1, 2 �CHANGE NO, 0328 DESCRXPTION EFFECTIVITIES STAGE GSE MILA 1, 2, 3 Rework the intertank umbilical locking mechanism - Reroute cable installation on fins B and D 2 -3 0330 Substitute amplifier used for ten mandatory prelaunch red line temperature measurements 3-15 0332 Rcvise the S-IC stage thrust structure hazardous gas detection system to provide sampling orifice in each quadrant 3-16 0333 Replace vibration transducers 60B72188-3 with 6OB72184-1 for 17 measurements in the engine area 2 -5 0335 Remove, retest, and re-identify all 65B23280 check valves 0308 Reviae F-f engine cocoon temperature 0329 MSE 1, 2 MTF 1 lWLA 1, 2, 3 3-16 transducer 0337 * Cancelled Replace resistors on printed circuit of telemetry oscillator assembly 11-15 0338 * Cancelled Replace the RN 55C1253F resistor in the 50M65485-1 printed wiring assembly in the subc a r r i e r oscillator assembly 11-15 0339 Correct cabling installation design deficiencies on S-IC stage 3 0344 Modify the fairing heat shield access panels 3-15 0345 Add weather protection covers to base a i r scoops 0346 Redesign the LOX overfill sensor 0347 Eliminate 17-7 PH mechanical feedback springs in Hydraulic Research S-IC servoactuator 3-15 0348 Eliminate single failure mode in outboard engine cutoff measurements for time base T-3 3-15 0349 T r i m engine fairing skin to prevent injury to personnel 0350 Provide attaching holes for hold down arms hood closure lanyard 1 D5-1260 1-5 �DESCRIPTION ClMMGE NO. EFFECTIVITIE$ GSE STAGE Modify servoactuator jack pin assembly 6351 MSE 1, 2 MTF 1 MILA 1, a 0362 * Cancelled 4 Provide special handling equipment at KSC 4-15 0353 Redesign of remote digital sub-multiplexer power supply 3-15 0354 Revise material of stage antifriction plates 3-15 0355 Provide additional vents for the servoactuator ancl Boeing suppBed engine thermal insulation 2-15 0356 Modify servoactuator boot fitting instauation to replace fasteners with through bolts 3-15 0357 Change 5-IC documentation to comply with KSC pull test requirements 2-3 6358 Provide positive moisture sealing of electrical cavities for the 60B49002 helium pressnrization and emergency dump valves 2-15 0359 Incorporate improved position switches in the LOX tank vent and relief valve f 6OB51002f 2-15 0360 Installation of the ordnance bracket assembly on the LOX and fuel tanks 2 -4 0362 Provide redundant electrical circuits to eliminate single failure modes in the engine cutoff system 3-15 0363 Protect electrical cables at entry (forward and aft} to stage from electrical tunnel 2-15 0365 Revise S-IC pneumatic console documentation MSE I, 2 MTO 1 MILA 1, 2, 3 MAB 110 KSC Geni 0367 Revise S-IC propellant dispersion system installation kit 0368* Cancel$& Delete brackets from LOX and fuel tanks 13-15 0369 Provide uninterrupted power (+28 VDC) to LOX -and fuel loading electronics 3-15 0370 Redesign of GOX feeder duct (603[351403-1) 3-15 D5-12601-5 �EFFECTNITIES STAGE GSE 0371 hlodify S-IC intertank umbilical lock mechanism MILA 1, 2, 3 0372 Modtfy the S-SC pneumatic cowole helium primary 'egulation circuit lMAB MTF 1 MILA 1, 2, 3 0373 * Cancelled Requirements for structural load monitoring at 9374 Revise the main seal in the LOX fill and drain valve 3-15 0375 Delete forward skirt umbilical door 4-15 0376 Reduce minimum pressure requirement for stage helium bottles and delete the helium bottles high pressure checkout switch 4-15 0377 Modify the S-IC storage racks to provide protection during launch MILA 1 0378 Provide additional fasteners for S-IC intertank umbilical reconnect assembly control box covers MILA 1, 2, 3 0379 Replace vent seals on all Airesearch prevalves and emergency drain valves 5-15 0381 * Cancelled Provide "power off" turbopump seal purge capability 3-15 0382 Eliminate He flow overlap of the stage and ground fuel tank pressurization system 2-15 0389 Eliminate water acceptanoe testing for Airesearch fuel prevalve 20PA32011-13 11-15 0385 Revise testing to prevent negative pressure in the S-IC LOX tank 2-15 0386 Change spring material in Whittaker LOX prevalves (2OM32010)and accomplish a modified requalification test 8-15 0387 Revise flight instrumentation to verify stage performance and environment 3-15 0388 Redesign electrical disconnect bracket (6OB67324-7) 3-5 0389 * Cancelled Modify filter manifold delta pressure transducer (Dl191 t u b a 3-15 C D5-12601-5 2-3 KSC MTO 1 MILA 1, 2, 3 MAB MSE 1, 2 MILA 1,2, 3 MTF 1 �CkiALANCE NO. DESCRIPTION Provide backup LOX bubbling system in the S-IC pneumatic console 0390 0392 EFFECTNM'IES STAGE GSE ' MTO 1 MAB MILA 1, 2, 3 Delete the S-IC base air scoop Provide a manual means to fill the stage hefirun bottles 0394 MAB MTQ 1 MXLA 1, 2, 3 Change O-rings in 65B23278 solenoid valves MSE 1, 2 MTF 1 MILA 1, 2, 3 0396 * Cancelled Block debris valves in S-IC intertank-reconnect assembly LOX fill and drain lines in the open position 0397 * Cancelled Change the material on the 60B41044 LOX fill and drain elbows 6015 0398 Provide for control of fuel and LOX loading electronics calibration commands from propellant tanking computer system 3-15 0399 Modlfy installation of acoustic vibration measurements utilizing 60B67632-XXX coaxial cable assembly 0400 Modi$ S-IC intertank umbilical reconnect assembly to include a backup retract capability MILA 1 MSE 1, 2 MTO 1 C 0401 112 Provide locking and position indicating mechanism for S-IC pneumatic oonsole and forward umbilical service unit manual ball valves MTF 1 MILA 1, 2, 3 MAB 0405 Modify the umbilical coupling for the oxidizer suction line bubbling system 0406 Modify TV objective lens housing assembly 0407 * Cancelled Readjust outboard LOX and fuel depletion system timers 2 0409 Provide hardwire engine actuator position interlock for engine cutoff 3-15 MSE 1, 2 MTO 1 0410 Modify engine cutoff circuitry to reduce potentiaI of premature shutdown 3-l6 MSE 1, 2 MTO 1 3-15 MSE 1, 2 MTF 1 MILA 1, 2, 3 D5-1260 1-5 �I -*. CHANGE NO. ' ' , DESCRIPTfON EPFECWITIEs BTAGE: 08E 0411 * Y rovide drain for servoactuator rod seal C ancelled leakage 0$12 Replace Southwestern Industries gage and absolute pressure switches with Consolidated Controls pressure switchers 3-15 0414 * cmcsw Replace bolts in fairing heat shield access panel 3-15 0415 Replace 5OM 04049 MOOG servoactuator with 60B84500 MOOG servoactaator 2 0419 Provide new htch on the S-IC intertank umbilical reconnect assembly 0421 Solder RF coaxial shield braid to connect shield clamp 3-8 0423 Y isual identification for S-IC stage ordnance 3-15 _ 2-15 M I U 1, 2,'3 AiLAB IVIIfLA 1, 2$ 8 systems I 0425 * C mcelted Modify fuel tank vertical internal access equipment 0426 Identification of equipment containers to twit 120 4-15 0428 * Propellant depletion system timer setting for S-IC-3 (B/P 30) 3 0429 * Add instrumentation for analysis of vehicle release condition 3 0430 Change frequency of telemetry links 6-15 0432 Modify LOX and fuel prepressurization syshms 0437 Lockwire threaded connectors which do Ifid have drilled holes for lockwiring 3-15 0441 Provide additional protection for components vulnerable to damage from the S-E/S-XI separation environment 3-15 0442 install helium injection POGO suppression systems 3-15 0444 Increase Ecmvard umbilical servioe unit flow cmilitg . G ancelled , D5-U60 1-5 I KSC Genl MSE 1, 2 MTO 1 MILA 1, 2, 3 MTO 1 MAD MSE 1, 2 MTO 1 MU 1 113 �CHANGE NO. DESCRfPTfON EFFECTNPTBS STAGE 0848 El Replace pressure gage in forward umbilical. service unit O866Rl Modify heater blanket assemblies 1-3 0867 R1 Modify base heat shield installation 1-15 W68 Rl Modify connector hex tlut 3-45 0869 R1 Eliminate interfe~enceon base air scoop measurement installation 1-5 0870 Rl Modify base heat shield support angle installation 1-4 0871 R1 Correct bolt lengths on lower fairings 3115 0873 R1 Modify support installation to allow installation of the recoverabie camera 2, 3 0874 R1 Correct bolt length on thrust structure base air scoop installation 1-15 0875 R1 Provide pilot relay for heater power contactor in S-IC pneumatic console 0876 RI Modify ground cable in TV camera system 2, 0875 R1 Mod* 1-15 0879 R1 Modify tube assembly in the pneumatic console 0880 R1 Eliminate an out-of-tolerance condition in the LOX leakmeter measurement F45-118 0883 R1 Correct bolt length callout on servoactuator boot installation 1-15 0884 R1 Modify length of cable assembly 115W305 1-5 0885 R1 LOX fill and drain valves (B-239,B240) control valves reversed cables retrorocket initiation system GSE LUT #I, 82, #3 MILA 1, 2, 3 MTF 1 3 MILA 1, 2, 3 MAB MTF 1 114 0887 Rl Calorimeter purge line clamp 0889 R1 Modify S-IC intedank umbilical to delay closure of debris valve 0890 R1 LOX arrd fuel loading electronics unit calibrai tion cablee 2 -5 MILA 1,2 D5-12601-6 �CHANGE NO, . a . E FFECTrVRTElS STAGE GSE DESCRIPTION 0891 R l Heat shield panel installation 2,3 bBQ2R1 Electrical installation forward skirt 293 0893 R l Eliminate leakage in LOX pressure sensing line MILA 1, 2, 3 0896 R l Housing Assembly aft 1 and 2 MfLA 1, 2, 3 0887 RZ Rebonding of antifriction plat;ee 2 0900 R1 Fuel delivery system installation fuel tank 1-15 0902 R1 Cable and instrument installation thrust chamber tmit 105 2-5 0903Rl Engine fairing blanket assembly 2-15 0904 R1 Cable and instrumentation installation units 101 and 102 0906 R1 Measurement installation fin B 2, 3 0907 R1 Propellant dispersion system installation and retrorocket initiation system 2-15 0908 R1 Change bolt callout 2-15 0913 R l Base heat shield bracket misalignment 3-15 0914 R1 Rework fuel ordnance cowling and revise ordnance installation requirements 2 -15 0916 ~i Rework thrust chamber insdation 2-5 0918 R1 Revise fin and fairing nut callouts 3-15 0920 R1 Replace insulation bracket covers 2-9 0929 R1 Disconnect position switch cables on vent and relief valves 2 1214 G Increase accuracy of GOX flow control valve pilot pressure measurement MSE 1, 2 1219 G Revision to stage handling equipment (MAB VAB) MAB 1221 G Utilize RCA llOA as primary engine test programmer MTF 1224 S Correct errors on LOX anti-vortex documenwon D54f2601-5 - 2-4 10-15 115 �CHANCE BO, DESCRDPTION EFFECTIVITIES STAGE GSE 1225 S Replace roller cams oh LOX interconnect support bracket installation 1226 G Modify MTF rotational brace MTF 1 1227 C Modify the MTF hydraulic terminal equipment MTF 1 1232 0 Modify pin puller assemblies a d adjustment MTF 1 4-15 l i n a p s assembly at MTF 1233 G Modify the area contamination detection system 1235 S Provide self-aligning capability for engine fairing turnbucMes 5-15 1236 S Redesign rate gyro heater blanket assembly 10-15 1237 S Relocate engine actuator electrical filter assembly 5-15 1238 S Revise S-IC servoactuator thermal insulation documentation 10-15 1239 S Revise 60B19612-1 static firing antifriction plates to facilitate removal 6-15 1240 G Provide capability for remote pressurization a d venting of the COX ducting system 1243 G Modify aluminum forward handling ring test requirements 7-15 Provide new presampling filter and modified power supply cards -15 Eliminate solder joints susceptible to cracks in electrical distributors 10-15 1244 S + Cancelled 1245 S MSE 1, 2 MTO 1 t. ��APPENDIX G - SYSTEMS TEST M T O DOCUMENT STATUS REPORT DOCUMENT NO, 5-10016-1 f)fi*11789-005 DOCUMENT TITLE STATUS BMTOEMERGENCYCONTROLPUM IN WORK BTACE BEQUENCE/QBERATI[QNE Pub3 FOR COMPLETED SATURN S-IC -5 D5-11789-008 STAGE SEQUENCE/OPERATIONS PLAN FOR SATURN S-fC -6 COMPLETED 05-11789-100 STAGE SEQUENCE/OPERATIONS PLAN FOR SATURN S-IC -- PROCEDURES AND INSTRUCTIONS FOR PROCESSING STAGES AT MTF COMPLETED D5-13034 S-IC S P E C U L TESTS COMPLETED D5-13034-3 LOX EMERGENCY DUMP LINE TEST CANCELLED D5-13034-38 S-IC BOOSTER STORAGE BUILDING FLOOR SETTLEMENT TEST COMPLETED D5-13034-39 POST EMERGENCY DRAIN LINE COLLAPSE, SPECIAL RP-1 TRANSFER TESTS IN WORK D5-13034-40 FUEL TANK DRAIN TESTS S-IC -D IN WORK D5-13034-41 TEST OF S-IC STATIC TEST STAND VENTILATION IN WORK D5-13034-42 RCA/IlOA BECKMAN COMPUTER PROGRAM DEVELOPMENT COMPLETED D5-13034-43 TEST OF HOLDDOWN ARM ANTI-FRICTION PLATE IN WORK D5-13034-45 ENVIRONMENTAL TEST, S-IC EAST OBSERVATION BUNKER IN WORK D5-13034-46 IN-PLACE GN2 ONE-HALF INCH BY-PASS LINE TEST INWORK D5-1304'747 HELIUM FLOW CONTROL VALVE FLOW RESPONSE TEST IN WORK 5 / D5-13034-48 118 SIMULATED ON2 ONE-HALF INCH BY-PASS LINE TEST W WORK D5-1260 1-5 �DOCUMENT NO. DOCUMENT TITLE STATUS - MTF D5-13743 FACILITIES MAINTENANCE PLAN D5-13781 FACILITIES mINTENANCE RECORD SYSTEM CANCELLED CONTAMINATION CONTROL OF S-IC IN WORK D5-13970 SYSTEMS AT MTF CANCELLED �GLOSSARY CRT Cathode ray tube AS Apollolsaturn CSA Computer Sciences Applications MTC Bwing A t CSM Central Stores Michoud BEAR Boeing Investigation and Corrective Action Request CY Calendar year DAF Data Acquisition Facility DDAS Digital data acquisition system DEE Digital even& evaluator - Test Center, ICSC , Florida CAM Change action memo CAR Corrective action request CCB Configuration Control Board CCP Contract change proposal CDDT Countdown Demonstration Test CDF Confined detonating: fuse CDR Critical design review CEI Contract end item CID Cable Interconnect diagram C U S S I CHANGE: If an engineering change deviates from the contract and must, therefore, be covered by contract revision, it is Class I. All Class I changes are processed by Engineering Change Proposal. Class I changes are specifically identified as such if one or more of the following is affected: (I) Part I CEI Specifications; (2) Contract price o r fee and contract guarantees, delivery, or test schedules; (3) Changes to Part lI CEI Specifications if any or the following are affected interchangeability, electrical interference, present adjustments, interfaces, computer programs, change in vendors, retrofit, requalification testing, and any change affecting high energy nuclear radiation sources. - CLASS If CHANGE: All changes that are not Class I. C/O Checkout CPFF Cost plus fixed fee f contract) CPZF Cost plus &cenW@fee (contrwt) 120 Discrete iddiscrete out DRD Docutnent requirements description DRL Document requirements list DTS Data transmission system EAMR Engineering Advance Material Releases EAPL Engineering assembly parts list ECM Engineering change memorandum ECP Engineering change proposal ECPR Engineering change proposal requirements E CS Environmental control system EDS Emergency detection system E/E Electrical/electronic EITP End item test plan EMC Electromagnetic compatibility EM0 Equipment management organization EMPL Engineering master parts list EO Engineering order EPRR Engineering parts release record EQA Equipment quality analysis ERS Experience retention study, also Equipment record system FACX First article configuration inspection D5- 12601-5 �FISC Flexible line~wshaped charge LSBRS Launch Systems Branch records system FM Frequency modulated (modulation) LUT Launch Umbilical Tower FY Fiscal year MAB Mechanical automation breadboard GETS Ground Gquipment Test Set MAF Michoud Assembly Facility GFE Government furnished equipment MAR Maintenance Action Revision GFP Govelmment furnished property MB NASA/MSFC-Boeing (jointly issued specification, drawing, o r part number) . GN2 Gaseous nitrogen COX Gaseous oxygen gPm Gallons per minute GSE Ground support equipment HLS Hydraulic load simulator (NLAB) HPA High pressure air HPG High pressure gas HPIW High pressure industrial water HPSU Hydraulic power supply unit ICD Interface control documentation ICE Instrument calibration equipment IDEP Interservice Data Exchange Program MBR . MSFC/Boeing relay (last letter represents type of part) MCMRP Minimum configuration management requirements plan MCL Measurement control laboratory MDS Malfunction detection system Manufacturing engineering MF Medium Frequency Michoud Michoud Assembly Facility, New Orleans, Louisiana MIG Mechanical inert gas (welding process) MRB M m r i e l Review Board MSC Manned Spaceflight Center, Houston, Texas MSE Manufacturer's support equipment (GSE to support manufacturing facility) MSE I Manufacturer's support equipment this test complex used for PSC and refurbishment of stages. MSE 11 Manufacturer's support equipment this test complex used for PMC of stages. MSFC Marshall Space Flight Center, Huntsville, Alabama 3 IRN Interface Revision Notice ITGE Integrated telemetry grouud equipment JOD Joint occupancy date KSC Kennedy Space Center, Florida KSI Kips per square inch KVA Kilovolt ampere - =I2 Liquid hydrogen LN Liquid nitrogen MTF Mississippi Test Facility, Mississippi LOX Liquid oxygen MTO LSB Launch Systems Branch Mississippi Test Operations (Boeing Systems Test organization responsible for MTF activities) 121 �:,- 1 i'9i A ' , 0 : National Aeronautics and Space Administration HC Numerical Control NBT Nondeshzlctive Test N/N Next IIiyher Part Number HME NitrogeRnlelium NPSII Not positive suction head OAT Overall test (procedure) 0bE3 On-Line data input system OWP Offset Doppler system PAM Pulse amplitude modulated PAR Part analysis report PART f CEI specifications set forth "detail design and performance requirements" for S-IC-F, S-IC-1 through S-IC-10, and all deliverable GSE at KSC QC Quality control QMT Quality Maintenance Test R&D Research and development RACS Remote automatic calibration system RAM Reliability Analysis Model RDC Reliability Data Center RMM Remote Digital Sub-Mult;lplexer RF Radio frequency RFP Request for proposal RP-I Fuel (kerosene) I I? f C NASA ' h h* R-QUAL Quality Laboratory, MSFC - . - PART Ef CEI specifications set forth "drawings and test requirements" for S-IC-3 on (does not affect S-IC-F , S-IC-1, S-IC-2, o r deliverable GSE) R-TEST Test Laboratory, MSFC SA Supplemental Agreement SCN Specification Change Notice SDC Status Display Center SE Support Equipment ST-MTF Systems test PCA Production control area PCC Program control center PCM Pulse code modulated PD Program Directive PERT Program evaluation and review technique PMC Post-manufacturing checkout p/N Part Number PRR Production revision record (a claas IT change) PSC Q&RA - MTF TCC Test control center TIG Tungsten inert gas (welding process) T/M Telemetry TVC Thrust Vector Control UCR Unsatisfactory Condition Report UER Unplanned event record VAB Vertical Assembly Building VISTA Visual Task Analysis Post-static checkout WAC Work Authorization Change Quality and Reliabiliw Assurance AP Delta p , differential pressure C 122 D5-1260 1-5 � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket. Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite. A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000066 Title A name given to the resource "Saturn V First Stage Annual Progress Report: Fiscal Year 1968." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. D5-12601-5 Description An account of the resource The report covers June 30, 1967 through June 27, 1968: Contract NAS8-5608, Schedules 1 and 1A, July 27, 1968. Prepared by J. P. Delaloye, Management Reporting and Analysis; Supervised by D. G. Valentine, Management Reporting and Analysis; Approved by R. F. Terry, Program Reports; D. H. Creim, Michoud, Program Planning and Reporting Manager; E. K. Cooper, S-IC Program Executive. Creator An entity primarily responsible for making the resource Delaloye, J. P. Boeing Aerospace Company. Space Division. Launch Systems Branch Date A point or period of time associated with an event in the lifecycle of the resource 1968-07-27 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Saturn launch vehicles Saturn S-1C stage Project management Type The nature or genre of the resource Annual reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 27, Folder 33 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074