Airworthiness Directive · Amendment 39-18903 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to The Boeing Company Model 767-200, -300, and -400ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-53A0264, Revision 1, dated April 25, 2016 (“ASB 767-53A0264 R1”).
(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.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin lap splices are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections to detect any crack in the fuselage skin at the skin lap splices, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
Except as specified by paragraph (i) of this AD, at the applicable times specified in paragraph 1.E., “Compliance,” of ASB 767-53A0264 R1: Do external surface high frequency eddy current (HFEC), internal surface HFEC, and external surface low frequency eddy current inspections, as applicable, to detect cracks in the fuselage skin lap splices, in accordance with the Accomplishment Instructions of ASB 767-53A0264 R1. If any crack is found during any inspection required by this AD, before further flight, repair in accordance with Part 8 of the Accomplishment Instructions of ASB 767-53A0264 R1. Repeat the inspections thereafter at the times specified in paragraph 1.E., “Compliance,” of ASB 767-53A0264 R1, as applicable.
Repairs identified in Part 8 of ASB 767-53A0264 R1 specify post-modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an AMOC.
Where ASB 767-53A0264 R1 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.
