Airworthiness directives › 2013-17-08
AD 2013-17-08 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, and 747SR series airplanes, certificated in any category, having line numbers 1 through 1419 inclusive; except for Model 747-400 series airplanes that have been modified into the Model 747-400 large cargo freighter configuration.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (g) of AD 2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010). For airplanes having line numbers 1 through 1304 inclusive: Inspect the airplane for cracks between stringers 23 and 31 per Boeing Alert Service Bulletin 747-53A2450, Revision 2, including Appendix A, dated January 4, 2001; or Boeing Alert Service Bulletin 747-53A2450, Revision 5, dated January 29, 2009; at the later of the applicable times specified in paragraph (h) or (i) of this AD, per table 1 to paragraphs (g) and (h) of this AD. Where there are differences between the AD and Boeing Alert Service Bulletin 747-53A2450, Revision 2, including Appendix A, dated January 4, 2001; or Boeing Alert Service Bulletin 747-53A2450, Revision 5, dated January 29, 2009; the AD prevails. Table 1 to Paragraphs (g) and (h) of this AD—Inspection Requirements Type of Inspection Area to Inspect (1) Detailed Visual Strap inner chords forward and aft of the web, and exposed web adjacent to the inner chords on station 2231 frame from stringers 23 through 31 per Figure 5 or Figure 6 of the service bulletins specified in paragraph (g) or (h) of this AD, as applicable. (2) Surface High Frequency Eddy Current (HFEC) Station 2231 inner chord angles at lower main sill interface per Figure 5 or Figure 6 of the service bulletins specified in paragraph (g) or (h) of this AD, as applicable. (3) Open Hole HFEC Station 2231 frame fastener locations per Figures 4 and 7, and either Figure 5 or 6 of the service bulletins specified in paragraph (g) or (h) of this AD, as applicable. (4) Surface HFEC Around fastener locations on station 2231 inner chords from stringers 23 through 31 per Figure 5 or Figure 6 of the service bulletins specified in paragraph (g) or (h) of this AD, as applicable. (5) Low Frequency Eddy Current (LFEC) Station 2231 frame strap in areas covered by the reveal per Figure 5 or Figure 6 of the service bulletins specified in paragraph (g) or (h) of this AD, as applicable. Note 1 to paragraph (g) of this AD: There is no terminating action currently available for the inspections required by paragraph (g) of this AD.
Unsafe condition
This AD was prompted by multiple reports of cracking outside of the previous inspection areas and a report of a crack that initiated at the aft edge of the inner chord rather than initiating at a fastener location. We are issuing this AD to detect and correct such cracks, which could cause damage to the adjacent body structure and could result in depressurization of the airplane in flight.
Affected ADs
This AD supersedes AD 2010-20-08, Amendment 39-16442 (75 FR 61337, October 5, 2010).
Read the original on the Federal Register →
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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