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Airworthiness directives › 2012-26-02

AD 2012-26-02 Airworthiness Directives; The Boeing Company Airplanes

2013-02-06
2013-01-02
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Airframe
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Applicability*9

This AD applies to The Boeing Company Model 737-300, −400, and −500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010.

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 2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005). At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD, perform detailed and eddy current inspections for cracking of the crown area of the fuselage skin in accordance with Part 1, including the “Note,” of the Work Instructions of Boeing Special Attention Service Bulletin 737-53-1234, Revision 1, dated March 31, 2005, except as provided by paragraph (j) of this AD. Doing the inspections required by paragraph (m) of this AD terminates the inspections required by this paragraph for the corresponding inspection areas. (1) Before the accumulation of the applicable total flight cycles specified in the “Threshold” column of Table 1 of Figure 1 of Boeing Special Attention Service Bulletin 737-53-1234, Revision 1, dated March 31, 2005. (2) Within 4,500 flight cycles after August 1, 2005 (the effective date of AD 2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005).

Unsafe condition

This AD was prompted by reports of cracking at the horizontal chem-mill steps away from the lap joints over the entire crown area, and vertical chem-mill cracks adjacent to the butt joints. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could cause the fuselage skin to fracture and fail, and result in rapid decompression of the airplane.

Affected ADs

This AD supersedes AD 2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005).

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