Airworthiness Directive · Amendment 39-18896 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1353, dated July 21, 2016.
(2) Installation of Supplemental Type Certificate (STC) ST00830SE [ http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/184DE9A71EC3FA5586257EAE00707DA6?OpenDocument&Highlight=st00830se ] does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE 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 certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the web lap splices in the aft pressure bulkhead are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the web lap splices in the aft pressure bulkhead for cracking of the fastener holes, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
Except as provided by paragraph (h) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1353, dated July 21, 2016: Do a low frequency eddy current (LFEC) inspection to detect cracking of each web lap splice of the aft pressure bulkhead at the fastener row common to the stiffener, and a high frequency eddy current (HFEC) inspection to detect cracking of each web lap splice of the aft pressure bulkhead at the fastener row not common to the stiffener, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1353, dated July 21, 2016.
(1) If no crack is found: Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1353, dated July 21, 2016.
(2) If any crack is found: Do the actions specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Repair the crack before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Although Boeing Alert Service Bulletin 737-53A1353, dated July 21, 2016, specifies to contact Boeing for repair instructions, and specifies that action as “RC” (Required for Compliance), this AD requires repair as specified in this paragraph.
(ii) On areas that are not repaired, repeat the inspections thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1353, dated July 21, 2016.
Where paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1353, dated July 21, 2016, 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.
