Airworthiness directives › 2016-04-07
AD 2016-04-07 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
(1) This AD applies to all The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01920SE ( http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0263, dated January 12, 2015, except as required by paragraph (h) of this AD, do external ultrasonic and detailed inspections to detect cracking, corrosion, or other damage at the splice fitting location, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0263, dated January 12, 2015. (1) If any cracking, corrosion, or other damage is not found, repeat the inspections at intervals not to exceed 6,000 flight cycles or 18,000 flight hours, whichever occurs first. Accomplishing a repair as specified in paragraph (g)(2) of this AD terminates the repetitive inspections in the repaired area only. (2) If any cracking, corrosion, or other damage is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. The repetitive inspections of paragraph (g)(1) are terminated in the repaired area only.
Unsafe condition
This AD was prompted by reports of cracking at a central part of the structure that includes the station 786 ring chord at the tension bolt hole common to the wing front spar lower chord and the internal bathtub fittings. We are issuing this AD to detect and correct fatigue cracking of the hidden fuselage skin and cracking, corrosion, and other damage to the splice fittings and adjacent visible fuselage skin and structure that could lead to loss of a primary load path between the fuselage and the wing box, and consequent reduced 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