Airworthiness Directive · Amendment 39-18698 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to The Boeing Company Model 757-200, -200CB, and -200PF series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015.
(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 superseding Airworthiness Directive (AD) 2006-20-11 for certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. AD 2006-20-11 required initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repair of any crack found. This new AD no longer allows the detailed inspections and instead requires repetitive external HFEC inspections for cracking of the skin lap splices of the fuselage, and repair if necessary. This AD was prompted by an evaluation done by the design approval holder (DAH) indicating that the fuselage skin lap splice is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2006-20-11, with terminating action. Do initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracking around the rivets at the upper fastener row of the skin lap splice of the fuselage by doing all the actions in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, except as provided by paragraphs (h) and (i) of this AD. Do the inspections at the applicable times specified in Paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005; except where Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, specifies a compliance time “after the original release date of this service bulletin,” this AD requires compliance after November 8, 2006 (the effective date of AD 2006-20-11). Accomplishing an inspection required by paragraph (j) of this AD terminates the inspections required by this paragraph.
This paragraph restates the requirements of paragraph (g) of AD 2006-20-11, with no changes. If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
This paragraph restates the provision specified in paragraph (h) of AD 2006-20-11, with no changes. Although Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, recommends that inspection results be reported to the manufacturer, this AD does not include that requirement.
At the applicable time specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015, except as provided by paragraphs (j)(1), (j)(2), and (l)(1) of this AD: Do an external HFEC inspection for cracking of the skin lap splices of the fuselage, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015. Repeat the inspection thereafter at the applicable times specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015. Doing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD.
(1) For airplanes on which Option 1 (detailed inspection) of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, has been done: Repeat the HFEC inspection before the accumulation of 37,500 total flight cycles, or within 3,000 flight cycles after accomplishing the most recent detailed inspection, whichever occurs later.
(2) For airplanes on which Option 2 (HFEC inspection) of Boeing Special Attention Service Bulletin 757-53-0090, dated June 2, 2005, has been done: Repeat the HFEC inspection before the accumulation of 37,500 total flight cycles, or within 12,000 flight cycles after accomplishing the most recent HFEC inspection, whichever occurs later.
If any cracking is found during any inspection required by paragraph (j) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(1) Where Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015, specifies a compliance time “after the Revision 1 date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) Although Boeing Special Attention Service Bulletin 757-53-0090, Revision 1, dated November 19, 2015, specifies to contact Boeing for repair instructions, and specifies that action as “RC” (Required for Compliance), paragraph (k) of this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) 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
