Airworthiness Directive · Amendment 39-17255 · Fuselage
The Boeing Company Airplanes
(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.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. 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. This AD requires repetitive inspections of the frame inner chord transition radius for cracks, and related investigative and corrective actions if necessary. 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.
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)).
(1) If any cracking is found during any inspection required by this AD, and Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(2) Where Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011, specifies a compliance time after the date on that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD.
Although Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
