Airworthiness directives › 2018-11-08
AD 2018-11-08 Airworthiness Directives; The Boeing Company Airplanes
Models named: 767-200, -300 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 767-200 and -300 series airplanes, as identified in Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 2017, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01920SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE 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
Except as required by paragraph (h) of this AD: At the applicable times specified in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 2017, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 2017. Note 1 to paragraph (g) of this AD: Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 767-53A0278, dated June 30, 2017, which is referred to in Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 2017.
Unsafe condition
This AD was prompted by a report of a crack on the transition radius of the station (STA) 883.5 frame inner chord and an additional crack indication at a fastener hole in the frame inner chord common to a material review board (MRB) filler that extended above the frame-to-stub-beam joint. We are issuing this AD to detect and correct cracking of the frame inner chord, which could result in the inability of one or more overwing stub frames between STA 808 and STA 933, each a principal structural element, to sustain limit loads; this condition could adversely affect the structural integrity of the airplane.
Affected ADs
None.
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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