Airworthiness Directive · Amendment 39-16775 · Wings
The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes
This AD applies to The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for cracking of the lower rear spar caps of the wings, and related investigative and corrective actions if necessary. This AD also requires repetitive inspections of certain repaired areas. This AD was prompted by reports of cracking of the wing rear spar lower cap at the outboard flap and inboard drive hinge at station Xrs=164.000; the cracking is due to material fatigue from normal flap operating loads. We are issuing this AD to detect and correct such fatigue cracking, which could result in fuel leaks, damage to the wing skin or other structure, and consequent reduced structural integrity of the wing.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the applicable times specified in paragraph 1.E. of Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011, do the actions required by paragraphs (g)(1) and (g)(2) of this AD, except as required by paragraph (i) of this AD. The actions specified in paragraphs (g)(1) and (g)(2) of this AD are not required for Group 1, Configuration 1 airplanes, as identified in Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011.
(1) Do initial and repetitive eddy current testing high frequency (ETHF) inspections for cracking of the lower rear spar caps of the wings, and do all applicable related investigative and corrective actions, by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011; or in accordance with the procedures specified in paragraph (k) of this AD.
(2) Do initial and repetitive ETHF inspections for cracking of any doubler repairs, and do all applicable related investigative and corrective actions, by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011; except as required by paragraph (j) of this AD.
Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin MD80-57A242, dated May 8, 2009, are acceptable for compliance with the corresponding requirements of this AD.
(i) Where Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011, specifies a compliance time after the date of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD.
(j) If any crack is found during any inspection of a doubler repair, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
