AD 52-27-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-6 | Airworthiness Directives; DOUGLAS DC-6 Aircraft |
| aircraft | The Boeing Company | DC-6A | Airworthiness Directives; DOUGLAS DC-6 Aircraft |
| aircraft | The Boeing Company | DC-6B | Airworthiness Directives; DOUGLAS DC-6 Aircraft |
Unsafe Condition
Cracks in the chordwise direction in the area of the milled radius of the aft attach tab of the lower front spar splice plate (Douglas P/N 4325272) at Station 166 in the area of the inboard nacelle.
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 the specified area. Stop drill and ream cracks less than 1 3/8 inches long, replace splice plates with cracks longer than 1 3/8 inches before next flight, and replace reworked plates within 1,500 flying hours. Continue inspections at intervals not exceeding 400 flying hours for reworked plates until replaced.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
As soon as practical but not later than the next 50 hours operation, continuing thereafter at intervals of regular inspection periods nearest to 500 flying hours until the splice plate is replaced.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Douglas Model DC-6 Aircraft (Fuselage Numbers 1 to 166, 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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