Airworthiness Directive · Amendment 39-15298 · McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) Airplanes
McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) Airplanes
This AD applies to McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006.
We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes. This AD requires, for certain airplanes, inspecting for cracking of the fuselage skin at the upper corners of the forward passenger doorjamb, installing or replacing doublers as applicable, and doing applicable repairs. This AD results from reports of fatigue cracking in the fuselage skin at the upper corners of the forward passenger doorjamb. We are issuing this AD to prevent cracking of the fuselage skin at the upper corners of the forward passenger doorjamb, which could lead to loss of overall 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.
For airplanes identified as Configuration 1, 2, or 3 in Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006: At the applicable times specified in paragraph 1.E., “Compliance,” of the alert service bulletin, do a low-frequency eddy current (LFEC) or high-frequency eddy current (HFEC) inspection, as applicable, for cracking of the fuselage skin at the upper corners of the forward passenger doorjamb; and do all applicable corrective actions (repetitive inspections, installation of doublers, replacements, and repairs), except as provided by paragraph (g) of this AD. Do the actions in accordance with the Accomplishment Instructions of the alert service bulletin. Where the alert 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.
If any crack is found during any inspection required by paragraph (f) of this AD and Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
For airplanes identified as Configuration 4 in Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006: Within 90 days after the effective date of this AD, repair using a method approved in accordance with the procedures specified in paragraph (i) of 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.
