AD 98-17-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-9-81 (MD-81) | Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes |
| aircraft | The Boeing Company | DC-9-82 (MD-82) | Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes |
| aircraft | The Boeing Company | DC-9-83 (MD-83) | Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes |
| aircraft | The Boeing Company | DC-9-87 (MD-87) | Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes |
| aircraft | The Boeing Company | MD-88 | Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes |
Unsafe Condition
Fatigue cracking of certain fuselage skin panels between stations Y=160.000 and Y=200.000 at the left side of longeron 22 below the airstair door cutout.
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Required Actions
Perform a high frequency eddy current (HFEC) inspection to detect fatigue cracking. If no cracking is found, continue inspections every 4,500 landings or install a preventative modification. If cracking is detected, install a temporary repair, conduct visual and HFEC inspections at specified intervals, and complete a permanent repair within 8,000 landings.
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Compliance Time
Prior to the accumulation of 44,500 total landings, or within 4,500 landings after the effective date of this AD, whichever occurs later.
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Affected Aircraft
McDonnell Douglas Model DC-9-80 series airplanes (DC-9-81, DC-9-82, DC-9-83, DC-9-87, MD-88) as listed in Service Bulletin 53-253.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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