AD 53-08-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-6 | Airworthiness Directives; DOUGLAS DC-6 Series Aircraft |
| aircraft | The Boeing Company | DC-6A | Airworthiness Directives; DOUGLAS DC-6 Series Aircraft |
| aircraft | The Boeing Company | DC-6B | Airworthiness Directives; DOUGLAS DC-6 Series Aircraft |
Unsafe Condition
Fatigue cracks in the center wing lower skin panel and stringers inboard of Station 60 at both sides of the two access doors (fore and aft).
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct inspections using an 8-power magnifying glass or dye check method for cracks in door doubler, bottom wing skin, and stringers. Repair cracks per Douglas Drawings 5460214, 5460328-501, or 5460328-1 depending on crack length and location. Install preventive reinforcements per Douglas Service Bulletin No. 521 Kits A-F based on fuselage numbers and inspection results.
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Compliance Time
As soon as practical but not later than the next 50 hours of operation, with subsequent inspections every 500 flying hours until permanent rework. Preventive reinforcements required no later than May 1, 1953 (fuselage 1-69) or September 1, 1953 (fuselage 70-213), whichever occurs first for fuselage 70-213 also considering 1,500 flying hours.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Douglas DC-6, DC-6A, DC-6B aircraft with fuselage numbers 1 to 213 inclusive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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