Airworthiness Directive · Amendment 39-13866 · McDonnell Douglas Model DC-9-14 and DC-9-15 Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes
McDonnell Douglas Model DC-9-14 and DC-9-15 Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes
Superseded. A later AD replaced this one: AD 2010-23-10. Comply with the one in force.
This AD applies to certain McDonnell Douglas Model DC-9-14, DC-9-15, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and DC-9-51 airplanes, certificated in any category; as listed in Boeing Service Bulletin DC9-57-223, dated July 21, 2003.
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-14 and DC-9-15 airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD requires repetitive high frequency eddy current inspections to detect cracks in the vertical radius of the upper cap of the center wing rear spar, and repair if necessary. This AD is prompted by reports of cracks in the upper cap of the center wing rear spar that resulted from stress corrosion. We are issuing this AD to detect and correct cracking of the left or right upper cap of the center rear spar, which would cause a possible fuel leak and structural failure of the upper cap, and result in reduced structural integrity of the airplane.
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 later of the times specified in paragraph (f)(1) or (f)(2) of this AD: Do a high frequency eddy current inspection to detect cracks in the vertical radius of the upper cap of the center wing rear spar, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC9-57-223, dated July 21, 2003.
(1) Before the accumulation of 25,000 total flight cycles.
(2) Within 15,000 flight cycles or 5 years after the effective date of this AD, whichever occurs first.
(g)(1) If no crack is found, then repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles or 5 years, whichever occurs first.
(2) If any crack is found, before further flight, repair per a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Los Angeles ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
