Airworthiness directives › 2012-08-14
AD 2012-08-14 Airworthiness Directives; The Boeing Company Airplanes
Models named: 767-200, -300, -300F, -400ER series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
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.
Unsafe condition
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. We are issuing this AD to detect and correct fatigue 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, 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.
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