Airworthiness Directive · Amendment 39-15045 · McDonnell Douglas 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
McDonnell Douglas 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
Superseded. A later AD replaced this one: AD 2023-02-09. Comply with the one in force.
This AD applies to all McDonnell Douglas 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.
The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas 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 requires repetitive inspections to detect cracks in the horizontal stabilizer, and related investigative/corrective actions if necessary. This AD results from reports of cracks found in the horizontal stabilizer--in the upper and lower aft skin panels at the aft inboard corner at station XH = 8.2, and in the rear spar upper caps adjacent to the aft skin panel at station XH = 10.0. We are issuing this AD to detect and correct cracks in the upper and lower aft skin panels and rear spar upper caps, which, if not corrected, could lead to the loss of overall structural integrity of the horizontal stabilizer.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Do eddy current inspections to detect cracks in the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-55A065, dated April 25, 2007.
(1) Do the initial inspections before the accumulation of 20,000 total flight cycles, or within 854 flight cycles after the effective date of this AD, whichever occurs later.
(2) Except as required by paragraphs (g) and (h) of this AD: Do all applicable repetitive inspections and related investigative and corrective actions in accordance with, and at the times specified in, the service bulletin.
Where Boeing Alert Service Bulletin MD80-55A065, dated April 25, 2007, specifies inspecting any skin panel splice or cap splice installed as part of a crack repair option: This AD requires the initial inspection within the compliance time specified in the service bulletin, but the inspection type, method, and repetitive interval must be done with FAA approval in accordance with the procedures specified in paragraph (i) of this AD.
(h) For airplanes on which any detected crack meets the Condition 2 criteria specified in Table 1 or Table 3 in paragraph 1.E. of Boeing Alert Service Bulletin MD80-55A065, dated April 25, 2007: If Option 1 or 2 is selected as the corrective action, either install a horizontal stabilizer aft skin panel splice or remove and replace the horizontal stabilizer aft skin panel within 4,000 flight cycles after accomplishing Option 1 or 2, in accordance with Option 3 or 4 of the applicable table, and repeat the inspection thereafter at the time specified in Option 3 or 4, as applicable.
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.
