Airworthiness directives › 2014-05-13
AD 2014-05-13 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 The Boeing Company Model 757-200, -200PF, and -200CB series airplanes, certificated in any category, line numbers 1 through 735 inclusive, equipped with Rolls-Royce RB211 engines. (2) Installation of Supplemental Type Certificate (STC) ST01518SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/48e13cdfbbc32cf4862576a4005d308b/Body/0.48A!OpenElement&FieldElemFormat=gif ) 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
This paragraph restates the requirements of paragraph (a) of AD 2004-12-07, Amendment 39-13666 (69 FR 33561, June 16, 2004), with new service information: Modify the nacelle strut and wing structure according to Boeing Service Bulletin 757-54-0035, dated July 17, 1997; Revision 1, dated April 15, 1999; Revision 2, dated June 13, 2002; or Revision 6, dated December 2, 2011; except as specified in paragraph (l) of this AD; at the later of the times specified in paragraph (g)(1) or (g)(2) of this AD, except as required by paragraph (i) of this AD. All of the terminating actions described in paragraph I.C., Table I, “Strut Improvement Bulletins,” on page 6 of Boeing Service Bulletin 757-54-0035, dated July 17, 1997; page 7 of Boeing Service Bulletin 757-54-0035, Revision 1, dated April 15, 1999; and on page 7 of Boeing Service Bulletin 757-54-0035, Revision 2, dated June 13, 2002; as applicable; must be accomplished prior to, or concurrently with, the accomplishment of the modification of the nacelle strut and wing structure required by this paragraph. After July 21, 2004 (the effective date of AD 2004-12-07), use only Boeing Service Bulletin 757-54-0035, Revision 2, dated June 13, 2002; or Boeing Service Bulletin 757-54-0035, Revision 6, dated December 2, 2011. After the effective date of this AD, use only Boeing Service Bulletin 757-54-0035, Revision 6, dated December 2, 2011. Accomplishment of the actions required by paragraph (i) of this AD terminates the requirements of this paragraph. (1) Prior to the accumulation of 37,500 total flight cycles, or prior to 20 years since the date of manufacture of the airplane, whichever occurs first. (2) Within 3,000 flight cycles after January 3, 2000 (the effective date of AD 99-24-07, Amendment 39-11431 (64 FR 66370, November 26, 1999)).
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. 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 2004-12-07, Amendment 39-13666 (69 FR 33561, June 16, 2004).
Read the original on the Federal Register →
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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