Airworthiness directives › 2013-18-08
AD 2013-18-08 Airworthiness Directives; The Boeing Company Airplanes
Models named: 737-200, -200C, -300, -400, -500 series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (a) of AD 2004-18-06, Amendment 39-13784 (69 FR 54206, September 8, 2004), with revised service information. For Groups 1 through 5 airplanes identified in Boeing Alert Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001: Before the accumulation of 35,000 total flight cycles, or within 4,500 flight cycles after October 13, 2004 (the effective date of AD 2004-18-06), whichever is later, do external detailed and eddy current inspections of the crown area and other known areas of fuselage skin cracking, in accordance with Part 1 and Figure 1 of the Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001; or in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009; except as provided by paragraph (o) of this AD. Repeat the external detailed and eddy current inspections at intervals not to exceed 4,500 flight cycles until paragraph (i), (j)(1)(i), (j)(1)(ii), (k), (l), or (m) of this AD has been done, as applicable. Although paragraph 1.D. of Boeing Alert Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001, references a reporting requirement, such reporting is not required by this AD. Accomplishing the actions required by paragraph (p) or (q) of this AD ends the repetitive requirements in this paragraph.
Unsafe condition
This AD was prompted by new findings of vertical cracks along chem-milled steps adjacent to the butt joints. We are issuing this AD to detect and correct fatigue cracking of the skin panels, which could result in sudden fracture and failure of the skin panels of the fuselage, and consequent rapid decompression of the airplane.
Affected ADs
This AD supersedes AD 2004-18-06, Amendment 39-13784 (69 FR 54206, September 8, 2004).
Read the original on the Federal Register →
You just looked this one up by hand
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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