Airworthiness directives › 2012-15-12
AD 2012-15-12 Airworthiness Directives; The Boeing Company Airplanes
Models named: 767-200, -300, -300F, -400ER series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to all The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category. Note 1 to paragraph (c) of this AD: Installation of Supplemental Type Certificate (STC) ST01920SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/082838ee177dbf62862576a4005cdfc0/$FILE/ST01920SE.pdf ) 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 provided by paragraphs (h)(2) and (h)(3) of this AD, at the applicable compliance time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-57A0126, Revision 2, dated March 12, 2012: Do a high frequency eddy current (HFEC) inspection to detect cracking of the underwing longeron fitting; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0126, Revision 2, dated March 12, 2012, except as provided by paragraph (h)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the underwing longeron fitting thereafter at the applicable compliance time and intervals specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-57A0126, Revision 2, dated March 12, 2012.
Unsafe condition
This AD was prompted by reports of cracks of the underwing longeron fittings in the wing center section. We are issuing this AD to detect and correct such cracking, which could result in loss of the primary load path between the fuselage and the wing box, and consequent catastrophic damage to the wing box and failure of the wing.
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