Airworthiness directives › 2016-09-13
AD 2016-09-13 Airworthiness Directives; The Boeing Company Airplanes
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 737-53A1339, dated August 12, 2014. (2) Installation of Supplemental Type Certificate (STC) ST01219SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf ) 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 required by paragraphs (i)(2) and (i)(3) of this AD: At the applicable times specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1339, dated August 12, 2014, do a medium frequency eddy current (MFEC) inspection for cracking on the left-side and right-side of the upper frame at station 360 between stringer 13 and stringer 14, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1339, dated August 12, 2014. If no cracking is found, repeat the inspections at the applicable times specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1339, dated August 12, 2014. Accomplishment of the actions specified in paragraph (j) of this AD terminates the repetitive inspections required by this paragraph at the modified area only. The initial and repetitive inspections required by this paragraph may be terminated in the area under repairs installed prior to the effective date of this AD, provided they meet the requirements of paragraph (g)(1) or (g)(2) of this AD. (1) Repairs were installed to eliminate previously found cracking and were approved by the Boeing Organization Designation Authorization (ODA) with an FAA Form 8100-9. (2) Repairs were installed for damage other than cracking that have been re-evaluated and approved by the Boeing ODA with an FAA Form 8100-9 that includes an alternative method of compliance (AMOC) statement to paragraph (h) of this AD.
Unsafe condition
This AD was prompted by reports of fatigue cracking found at the left-side and right-side upper frames, at station 360 between stringer 13 and stringer 14. We are issuing this AD to detect and correct fatigue cracking of the upper frame, which can grow in size and result in a severed frame, leading to rapid decompression and consequent reduced 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