Airworthiness directives › 2017-17-06
AD 2017-17-06 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 737-53A1357, dated August 9, 2016. (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
Before the accumulation of 34,000 total flight cycles or within 6,000 flight cycles after the effective date of this AD, whichever occurs later, do a high frequency eddy current (HFEC) inspection for any cracking in the fuselage frame at station (STA) 947.5 common to the water tank support intercostal clip located between stringers S-24R and S-25R, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1357, dated August 9, 2016. (1) If no cracking is found, repeat the inspection thereafter at intervals not to exceed 12,000 flight cycles. (2) If any cracking is found: Before further flight, repair in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1357, dated August 9, 2016.
Unsafe condition
This AD was prompted by a report of fatigue cracking found in a certain fuselage frame common to the water tank support intercostal clip located between certain stringers. We are issuing this AD to detect and correct cracking, which could grow in size and result in a severed frame. Multiple adjacent severed frames would result in 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