Airworthiness Directive · Amendment 39-17031 · Wings
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 767-57A0117, Revision 1, dated March 2, 2011.
Note 1 to paragraph (c) of this AD: 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 according to paragraph (j) of this AD.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracking in the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar, which could result in the loss of the strut-to-wing upper link load path and possible separation of a strut and engine from the airplane during flight. This AD requires repetitive inspections to detect fatigue cracking in the wing skin, and corrective actions if necessary. We are issuing this AD to correct the unsafe condition on these products.
Except as provided by paragraph (h) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-57A0117, Revision 1, dated March 2, 2011: Do detailed and ultrasonic inspections, or do an open-hole high-frequency eddy current inspection, as applicable, to detect cracking in the upper surface of the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0117, Revision 1, dated March 2, 2011, except as required by paragraph (h) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspections thereafter at intervals not to exceed the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-57A0117, Revision 1, dated March 2, 2011.
(1) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 767-57A0117, Revision 1, dated March 2, 2011, specifies to contact Boeing for additional instructions: 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 Alert Service Bulletin 767-57A0117, Revision 1, dated March 2, 2011, specifies a compliance time after the date of the original issue of Boeing Alert Service Bulletin 767-57A0117, dated October 1, 2009: This AD requires compliance within the specified compliance time after the effective date of this AD.
