Airworthiness directives › 2016-22-09
AD 2016-22-09 Airworthiness Directives; The Boeing Company Airplanes
Models named: 757-200, -200CB, -200PF series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(1) This AD applies to The Boeing Company Model 757-200, -200CB, and -200PF series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015. (2) Installation of Supplemental Type Certificate (STC) ST01518SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38B606833BBD98B386257FAA00602538?OpenDocument&Highlight=st01518se ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (f) of AD 2006-20-11, with terminating action. Do initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracking around the rivets at the upper fastener row of the skin lap splice of the fuselage by doing all the actions in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, except as provided by paragraphs (h) and (i) of this AD. Do the inspections at the applicable times specified in Paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005; except where Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, specifies a compliance time “after the original release date of this service bulletin,” this AD requires compliance after November 8, 2006 (the effective date of AD 2006-20-11). Accomplishing an inspection required by paragraph (j) of this AD terminates the inspections required by this paragraph.
Unsafe condition
This AD was prompted by an evaluation done by the design approval holder indicating that the fuselage skin lap splice is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane.
Affected ADs
This AD replaces AD 2006-20-11, Amendment 39-14781 (71 FR 58485, October 4, 2006) (“AD 2006-20-11”). This AD affects AD 2006-11-11, Amendment 39-14615 (71 FR 30278, May 26, 2006) (“AD 2006-11-11”).
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