Airworthiness directives › 2016-20-14
AD 2016-20-14 Airworthiness Directives; The Boeing Company Airplanes
Models named: 737-600, -700, -700C, -800, -900, -900ER series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015: Do an external high frequency eddy current (HFEC) inspection for cracking of the skin around the fastener locations at the upper forward and lower aft corners of each window between station (STA) 360 and STA 540, as applicable, and at the lower forward and upper aft corners of each window between STA 727 and STA 887, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015. Repeat the inspection thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015. If any crack is found during any inspection, repair before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
Unsafe condition
This AD was prompted by an evaluation by the design approval holder indicating that certain fastener locations in the window corner surround structure are subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking around certain fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and consequent loss of structural integrity of the airplane.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1