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Airworthiness directives › 2017-15-12

AD 2017-15-12 Airworthiness Directives; The Boeing Company Airplanes

2017-09-05
2017-08-01
39-18972
FAA-2017-0330
Airframe
—

Models named: 737-300, -400, -500 series. Read the applicability below — it usually turns on serial or part numbers too.

Applicability*9

(1) This AD applies to The Boeing Company Model 737-300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1365, dated January 23, 2017. (2) Installation of Supplemental Type Certificate (STC) ST01219SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=st01219se ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE 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

Except as provided by paragraph (i) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1365, dated January 23, 2017: Do external eddy current inspections at stringer S-14 on the left and right sides of the airplane (S-14L and S-14R) for any crack in the skin lap splice at the lower fastener row, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1365, dated January 23, 2017. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1365, dated January 23, 2017.

Unsafe condition

This AD was prompted by an evaluation by the design approval holder indicating that the lower skin at the skin lap splice lower fastener row is subject to widespread fatigue damage. We are issuing this AD to detect and correct cracks in the lower skin, which, if not detected, could link up, resulting in reduced structural integrity of the airplane and consequent uncontrolled decompression 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