Airworthiness Directive · Amendment 39-17141 · Wings
The Boeing Company Airplanes
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.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracks of the underwing longeron fittings in the wing center section. This AD requires repetitive inspections of the underwing longeron fitting for cracking, and related investigative and corrective actions if necessary. 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.
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.
(1) If, during accomplishment of the related investigative action required by this AD, any cracking is found and Boeing Alert Service Bulletin 767-57A0126, Revision 2, dated March 12, 2012, specifies to contact Boeing for repair instructions: Before further flight, do the repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(2) Where Paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-57A0126, Revision 2, dated March 12, 2012, specifies a compliance time “after the original issue date of this service bulletin,” this AD requires compliance within the specified compliance time “after the effective date of this AD.”
(3) The Condition column of Paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-57A0126, Revision 2, dated March 12, 2012, refers to total flight cycles and total flight hours “as of the original issue date of this service bulletin.” However, this AD applies to the airplanes with the specified total flight cycles or total flight hours “as of the effective date of this AD.”
