Airworthiness Directive · Amendment 39-18702 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC) ST00830SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38B606833BBD98B386257FAA00602538?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 all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that lap splices for certain stringers are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking in the lower fastener row of the lap splices of certain stringers, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
At the applicable compliance time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1352, Revision 1, dated March 10, 2016, do a low frequency eddy current inspection for cracking of the lower fastener row of S-14L and S-14R lap splices, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1352, Revision 1, dated March 10, 2016. Repeat the inspection thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1352, Revision 1, dated March 10, 2016. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
