Airworthiness Directive · Amendment 39-18595 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 757-200 and -200CB series airplanes, certificated in any category.
(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.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200 and -200CB series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices at stringer S-14R, lower fastener row, are subject to widespread fatigue damage (WFD). This AD requires external dual frequency eddy current (DFEC) or internal high frequency eddy current (HFEC) inspections of the lap splice, inner skin fasteners, at stringer S-14R, station (STA) 440 through STA 540, and corrective action if necessary. We are issuing this AD to detect and correct cracking of the fuselage skin lap splice. Such cracking could result in reduced structural integrity of the airplane.
At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015, except as required by paragraph (h) of this AD: Do an external dual frequency eddy current inspection or internal high frequency eddy current inspection for cracking of the lap splice, inner skin lower fastener row, at stringer S-14R, station (STA) 440 through STA 540, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015. Repeat either inspection thereafter at the time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015.
Where Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015, 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.
If any crack is found during any inspection required by this AD, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
