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Airworthiness directives › 2013-10-02

AD 2013-10-02 Airworthiness Directives; The Boeing Company Airplanes

2013-06-20
2013-05-16
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Airframe
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Models named: 757-200, -200PF 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 757-200 and -200PF series airplanes, certificated in any category, line numbers 1 through 735 inclusive, powered by Pratt & Whitney engines. (2) 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. For all other AMOC requests, the operator must request approval for an AMOC in accordance with the provisions of paragraph (k) of this AD.

Compliance

Comply with this AD within the compliance times specified, unless already done.

Required actions

This paragraph restates the requirements of paragraph (a) of AD 2003-18-05, Amendment 39-13296 (68 FR 53496, September 11, 2003), with new service information and a reduced compliance time. Modify the nacelle strut and wing structure on both the left and right sides of the airplane, in accordance with Boeing Service Bulletin 757-54-0034, dated May 14, 1998; Boeing Service Bulletin 757-54-0034, Revision 1, dated October 11, 2001; or Boeing Service Bulletin 757-54-0034, Revision 2, dated May 7, 2009; at the later of the times specified in paragraph (g)(1) or (g)(2) of this AD. As of the effective date of this AD, only Boeing Service Bulletin 757-54-0034, Revision 2, dated May 7, 2009, may be used to accomplish the actions required by this paragraph. (1) At the earlier of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Prior to the accumulation of 37,500 total flight cycles. (ii) At the later of the times specified in paragraph (g)(1)(ii)(A) or (g)(1)(ii)(B) of this AD. (A) Within 20 years since the date of manufacture. (B) Within the compliance time calculated using the optional threshold formula described in Boeing Service Bulletin 757-54-0034, Revision 2, dated May 7, 2009, or within 8 years after the effective date of this AD, whichever occurs first. (2) Within 3,000 flight cycles after November 13, 2000 (the effective date of AD 2000-20-09, Amendment 39-11920 (65 FR 59703, October 6, 2000)).

Unsafe condition

This AD was prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. Subsequent analysis and service history, which includes numerous reports of fatigue cracking on certain strut and wing structure, indicated that fatigue cracking can occur on the primary strut structure before an airplane reaches its design service objective. We are issuing this AD to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut.

Affected ADs

This AD supersedes AD 2003-18-05, Amendment 39-13296 (68 FR 53496, September 11, 2003).

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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