Post-fire Structural Integrity Evaluation of an Aircraft Utilizing ASTM E 1004-02
Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
McDougall, Jeffrey L. [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2015 |
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| Schlagwörter: |
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| Anmerkung: |
© ASM International 2015 |
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| Übergeordnetes Werk: |
Enthalten in: Practical failure analysis - Springer New York, 2001, 15(2015), 1 vom: 13. Jan., Seite 3-6 |
|---|---|
| Übergeordnetes Werk: |
volume:15 ; year:2015 ; number:1 ; day:13 ; month:01 ; pages:3-6 |
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| DOI / URN: |
10.1007/s11668-014-9920-5 |
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| 520 | |a Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. | ||
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10.1007/s11668-014-9920-5 doi (DE-627)SPR02167115X (SPR)s11668-014-9920-5-e DE-627 ger DE-627 rakwb eng McDougall, Jeffrey L. verfasserin aut Post-fire Structural Integrity Evaluation of an Aircraft Utilizing ASTM E 1004-02 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2015 Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. Aircraft (dpeaa)DE-He213 Fire damage (dpeaa)DE-He213 Aluminum (dpeaa)DE-He213 Eddy current (dpeaa)DE-He213 Materials testing (dpeaa)DE-He213 Klepacki, David G. aut Stevenson, Michael E. aut Kenner, Matthew T. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2015), 1 vom: 13. Jan., Seite 3-6 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2015 number:1 day:13 month:01 pages:3-6 https://dx.doi.org/10.1007/s11668-014-9920-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2015 1 13 01 3-6 |
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10.1007/s11668-014-9920-5 doi (DE-627)SPR02167115X (SPR)s11668-014-9920-5-e DE-627 ger DE-627 rakwb eng McDougall, Jeffrey L. verfasserin aut Post-fire Structural Integrity Evaluation of an Aircraft Utilizing ASTM E 1004-02 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2015 Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. Aircraft (dpeaa)DE-He213 Fire damage (dpeaa)DE-He213 Aluminum (dpeaa)DE-He213 Eddy current (dpeaa)DE-He213 Materials testing (dpeaa)DE-He213 Klepacki, David G. aut Stevenson, Michael E. aut Kenner, Matthew T. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2015), 1 vom: 13. Jan., Seite 3-6 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2015 number:1 day:13 month:01 pages:3-6 https://dx.doi.org/10.1007/s11668-014-9920-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2015 1 13 01 3-6 |
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10.1007/s11668-014-9920-5 doi (DE-627)SPR02167115X (SPR)s11668-014-9920-5-e DE-627 ger DE-627 rakwb eng McDougall, Jeffrey L. verfasserin aut Post-fire Structural Integrity Evaluation of an Aircraft Utilizing ASTM E 1004-02 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2015 Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. Aircraft (dpeaa)DE-He213 Fire damage (dpeaa)DE-He213 Aluminum (dpeaa)DE-He213 Eddy current (dpeaa)DE-He213 Materials testing (dpeaa)DE-He213 Klepacki, David G. aut Stevenson, Michael E. aut Kenner, Matthew T. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2015), 1 vom: 13. Jan., Seite 3-6 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2015 number:1 day:13 month:01 pages:3-6 https://dx.doi.org/10.1007/s11668-014-9920-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2015 1 13 01 3-6 |
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10.1007/s11668-014-9920-5 doi (DE-627)SPR02167115X (SPR)s11668-014-9920-5-e DE-627 ger DE-627 rakwb eng McDougall, Jeffrey L. verfasserin aut Post-fire Structural Integrity Evaluation of an Aircraft Utilizing ASTM E 1004-02 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2015 Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. Aircraft (dpeaa)DE-He213 Fire damage (dpeaa)DE-He213 Aluminum (dpeaa)DE-He213 Eddy current (dpeaa)DE-He213 Materials testing (dpeaa)DE-He213 Klepacki, David G. aut Stevenson, Michael E. aut Kenner, Matthew T. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2015), 1 vom: 13. Jan., Seite 3-6 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2015 number:1 day:13 month:01 pages:3-6 https://dx.doi.org/10.1007/s11668-014-9920-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2015 1 13 01 3-6 |
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10.1007/s11668-014-9920-5 doi (DE-627)SPR02167115X (SPR)s11668-014-9920-5-e DE-627 ger DE-627 rakwb eng McDougall, Jeffrey L. verfasserin aut Post-fire Structural Integrity Evaluation of an Aircraft Utilizing ASTM E 1004-02 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © ASM International 2015 Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. Aircraft (dpeaa)DE-He213 Fire damage (dpeaa)DE-He213 Aluminum (dpeaa)DE-He213 Eddy current (dpeaa)DE-He213 Materials testing (dpeaa)DE-He213 Klepacki, David G. aut Stevenson, Michael E. aut Kenner, Matthew T. aut Enthalten in Practical failure analysis Springer New York, 2001 15(2015), 1 vom: 13. Jan., Seite 3-6 (DE-627)886125871 (DE-600)2893589-5 5555-1313 nnns volume:15 year:2015 number:1 day:13 month:01 pages:3-6 https://dx.doi.org/10.1007/s11668-014-9920-5 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 15 2015 1 13 01 3-6 |
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Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. © ASM International 2015 |
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Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. © ASM International 2015 |
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Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced. © ASM International 2015 |
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<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">SPR02167115X</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230331060323.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">201006s2015 xx |||||o 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/s11668-014-9920-5</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)SPR02167115X</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(SPR)s11668-014-9920-5-e</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">McDougall, Jeffrey L.</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Post-fire Structural Integrity Evaluation of an Aircraft Utilizing ASTM E 1004-02</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2015</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© ASM International 2015</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Abstract During maintenance, a post-World War II military training airplane experienced a ground fire that resulted in damage to the lower fuselage forward of the wing spar carry-through structure. Although the fire was contained approximately 18 in. forward of the carry-through structure, existing airworthiness concerns and the critical nature of this area resulted in the need to evaluate the possibility of damage resulting from the fire. A correlation between the electrical conductivity and mechanical properties of the aluminum structure was established from components that were fire damaged and, consequently, removed during repair of the aircraft. This correlation was then used to non-destructively evaluate the integrity of the material in the carry-through structure and, ultimately, confirmed that the carry-through structure did not have to be replaced.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Aircraft</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Fire damage</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Aluminum</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Eddy current</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Materials testing</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Klepacki, David G.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Stevenson, Michael E.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Kenner, Matthew T.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Practical failure analysis</subfield><subfield code="d">Springer New York, 2001</subfield><subfield code="g">15(2015), 1 vom: 13. 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