Airworthiness directives › 2013-24-11
AD 2013-24-11 Airworthiness Directives; The Boeing Company Airplanes
Models named: 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; certificated in any category; as identified in Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012, except as required by paragraphs (i)(1) and (i)(3) of this AD: Do the applicable inspections (including detailed, high frequency eddy current (HFEC), and low frequency eddy current (LFEC)) for any cracking of the fuselage skin, for discrepant fasteners, and for disbonds at the doublers; and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012, except as provided by paragraph (i)(2) of this AD. Repeat the applicable inspections thereafter at intervals not to exceed those specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012. Do all applicable related investigative and corrective actions at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012. Options provided in Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2011, for accomplishing the disbond inspection are acceptable for the corresponding requirements of this paragraph provided that the inspection is done at the applicable times in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2011. (1) Replacing a skin panel, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012, is an acceptable alternative to doing the structural repair manual (SRM) skin panel repairs and the repetitive skin panel inspections specified in tables 1, 2, and 3 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012, for only the skin panel that has been replaced. (2) Accomplishment of the terminating repair identified in tables 4 and 5 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012, terminates the repetitive inspections identified in tables 4 and 5 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2747, Revision 2, dated February 22, 2012, for only the area on which the terminating repair has been done.
Unsafe condition
This AD was prompted by a disbonded doubler and a skin crack in section 41 of the fuselage, and multiple reports of cracked or missing fastener heads. We are issuing this AD to prevent rapid decompression and loss of structural integrity of the airplane due to such disbonding and subsequent cracking of the skin panels.
Affected ADs
This AD affects AD 2006-20-02, Amendment 39-14771 (71 FR 56861, September 28, 2006); AD 2006-24-02, Amendment 39-14831 (71 FR 67445, November 22, 2006); and AD 2006-24-05, Amendment 39-14834 (71 FR 68434, November 27, 2006).
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1