Airworthiness directives › 2012-22-17
AD 2012-22-17 Airworthiness Directives; The Boeing Company Airplanes
Models named: 767-200, -300 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 767-200 and -300 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011. (2) Supplemental Type Certificate (STC) ST01920SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/082838ee177dbf62862576a4005cdfc0/$FILE/ST01920SE.pdf ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE 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 procedures specified in paragraph (j) of this AD.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Except as required by paragraph (h)(2) of this AD, at the times specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011: Perform a detailed inspection or a surface high frequency eddy current (HFEC) inspection for cracking in the frame inner chord transition radius at stations 859.5, 883.5, and 903.5, as applicable, left buttock line and right buttock line 89, below water line 200; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011; except as required by paragraph (h)(1) of this AD. Do all applicable related investigative and corrective actions before further flight. If no cracking is found, repeat the inspections thereafter at the applicable interval specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011. Note 1 to paragraph (g) of this AD: The post-repair inspections specified in Tables 2, 4, 6, and 8 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011, may be used in support of compliance with paragraph (c)(2) of Section 121.1109 or 129.109 of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(c)(2)).
Unsafe condition
This AD was prompted by reports of cracks in the inner chords at both left-side and right-side stations 859.5, 883.5, and 903.5. We are issuing this AD to prevent large cracks in the frames and adjacent structure that can adversely affect the 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