AD 2005-14-10
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | McDonnell Douglas | DC-10-10 and DC-10-10F | Airworthiness Directives; McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; and Model DC-10-40 and DC-10-40F Airplanes |
Unsafe Condition
Fatigue cracking in baseline structure that could compromise the structural integrity of the airplanes as they approach the manufacturer's original fatigue design life goal.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Implement a program of structural inspections to detect and correct fatigue cracking. Inspections must be conducted at specified intervals, including at or near the threshold (Nth) and every ΔNDI/2 thereafter. Discrepant principal structural elements (PSEs) must be repaired before further flight, with a grace period of 18 months for repairs meeting static strength requirements.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 60 months after the effective date of the AD, or before reaching the threshold (Nth) or ΔNDI/2, whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, and DC-10-40F airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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