Airworthiness directives › 2014-22-10
AD 2014-22-10 Airworthiness Directives; The Boeing Company Airplanes
Models named: DC-8-55, DC-8F-54, DC-8F-55, DC-8-61, DC-8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-63F, DC-8-71. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to The Boeing Company airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, as identified in Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated September 18, 2013. (1) The Boeing Company Model DC-8-55 airplanes. (2) The Boeing Company Model DC-8F-54 and DC-8F-55 airplanes. (3) The Boeing Company Model DC-8-61, DC-8-62, and DC-8-63 airplanes. (4) The Boeing Company Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes. (5) The Boeing Company Model DC-8-71, DC-8-72, and DC-8-73 airplanes. (6) The Boeing Company Model DC-8-71F, DC-8-72F, and DC-8-73F airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Before the accumulation of 45,400 total flight cycles, or within 72 months after the effective date of this AD, whichever occurs later: Remove any previously installed local repairs and install a full-length improvement modification with or without finger doublers, or a full-length repair with or without finger doublers, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated September 18, 2013. Installation of the full-length improvement modification or full-length repair, in accordance with paragraph (i) of AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008), is a method of compliance with the requirements of this paragraph. Installation of a local repair as specified in paragraph (i) of AD 2008-06-23, does not comply with the requirements of this paragraph.
Unsafe condition
This AD was prompted by multiple reports of cracking of the upper aft skin panel of the fuselage. An evaluation by the design approval holder indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane.
Affected ADs
None.
Read the original on the Federal Register →
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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