Airworthiness Directive · Amendment 39-15773 · McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series Airplanes; Model DC-8-70 Series Airplanes; and Model DC-8-70F Series Airplanes
McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series Airplanes; Model DC-8-70 Series Airplanes; and Model DC-8-70F Series Airplanes
Superseded. A later AD replaced this one: AD 2016-04-21. Comply with the one in force.
This AD applies to all McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, 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, DC-8-72, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes; certificated in any category.
We are adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires repetitive inspections of the lower skin and stringers at stations Xw=408 and Xw=-408, and corrective actions if necessary. This AD results from reports of cracks in the skins and stringers at the end fasteners common to the stringer end fittings at stations Xw= 408 and Xw=-408 wing splice joints. We are issuing this AD to detect and correct fatigue cracking in the skins and stringers at the end fasteners common to the stringer end fittings at certain station and wing splice joints, which could result in wing structure that might not sustain limit load, and consequent loss of structural integrity of the wing.
Comply with this AD within the compliance times specified, unless already done.
At the times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008 (“the service bulletin”), except as provided by paragraph (g) of this AD: Do the applicable inspections for fatigue cracking of the lower skin and stringers at stations Xw=408 and Xw=−408, and do all applicable corrective actions, by accomplishing all applicable actions specified in the Accomplishment Instructions of the service bulletin, except as provided by paragraph (h) of this AD. Do all corrective actions before further flight, in accordance with the service bulletin. Thereafter, repeat the inspections at the applicable intervals specified in paragraph 1.E. of the service bulletin.
(g) Where Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008 (“the service bulletin”), specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD.
(h) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, 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 (i) of this AD.
