Airworthiness directives › 2017-12-12
AD 2017-12-12 Airworthiness Directives; The Boeing Company Airplanes
Models named: 757-200, -200PF, -200CB 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 757-200, -200PF, and -200CB series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01518SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/48e13cdfbbc32cf4862576a4005d308b/$FILE/ST01518SE.pdf ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE 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 757-53A0105, dated June 10, 2016, except as required by paragraph (h)(1) of this AD: Do an LFEC inspection for cracking of the circumferential splice plates at station 900 and station 1180, from stringer S-6L to stringer S-6R, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016, except as required by paragraph (h)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016. Accomplishing these inspections terminates the requirements of paragraph (h) of AD 2006-11-11 for the inspections of structurally significant item (SSI) 53-40-05, circumferential skin splice body station BS900 stringer S-6L to stringer S-6R and circumferential skin splice body station BS1180 stringer S-6L to stringer S-6R, as specified in Section 9 of Boeing Maintenance Planning Data (MPD) Document D622N001-9, May 2003 or June 2005 revisions. All other requirements of AD 2006-11-11 remain fully applicable and must be complied with.
Unsafe condition
This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage circumferential splice plates along the center fastener rows, forward and aft of station 900 and station 1180 splice centerlines, are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct cracks of certain circumferential splice plates, which could lead to the failure of a principal structural element and could adversely affect the structural integrity of the airplane.
Affected ADs
This AD affects AD 2006-11-11, Amendment 39-14615 (71 FR 30278, May 26, 2006) (“AD 2006-11-11”).
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