Airworthiness directives › 2013-25-12
AD 2013-25-12 Airworthiness Directives; The Boeing Company Airplanes
Models named: DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to The Boeing Company Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes, and DC-9-41 airplanes, certificated in any category, identified in McDonnell Douglas DC-9 Alert Service Bulletin A53-144, Revision 2, dated February 23, 1984.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
For airplanes on which the modification (AD4 rivets replaced with AD5 rivets) required by AD 85-01-02 R1, Amendment 39-5241 (51 FR 6101, dated February 20, 1986), has not been done: Before the accumulation of 72,000 total flight cycles, or within 18 months after the effective date of this AD, whichever occurs later, modify the aft pressure bulkhead by removing all affected AD4 rivets and doing either a fluorescent penetrant or eddy current inspection around the rivet holes for cracks, repairing any cracking, and installing five-leaf doublers with AD5 rivets, in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Alert Service Bulletin A53-144, Revision 2, dated February 23, 1984; except as required by paragraph (h) of this AD. Note 1 to paragraph (g) of this AD: Information on additional procedures for the modification can be found in Notes 4, 5, and 6, as applicable, of paragraph 1.D., “Compliance” of McDonnell Douglas DC-9 Alert Service Bulletin A53-144, Revision 2, dated February 23, 1984.
Unsafe condition
This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage bulkhead web area is subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking of the bulkhead, which could result in 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