AD 49-38-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | C54-DC | Airworthiness Directives; DOUGLAS All Models C-54 and DC-4 Aircraft |
| aircraft | The Boeing Company | C54A-DC | Airworthiness Directives; DOUGLAS All Models C-54 and DC-4 Aircraft |
| aircraft | The Boeing Company | C54B-DC | Airworthiness Directives; DOUGLAS All Models C-54 and DC-4 Aircraft |
| aircraft | The Boeing Company | C54D-DC | Airworthiness Directives; DOUGLAS All Models C-54 and DC-4 Aircraft |
| aircraft | The Boeing Company | C54E-DC | Airworthiness Directives; DOUGLAS All Models C-54 and DC-4 Aircraft |
| aircraft | The Boeing Company | C54G-DC | Airworthiness Directives; DOUGLAS All Models C-54 and DC-4 Aircraft |
| aircraft | The Boeing Company | DC-4 | Airworthiness Directives; DOUGLAS All Models C-54 and DC-4 Aircraft |
Unsafe Condition
Fatigue failure of critical structural bolts in fuselage, wing, stabilizer, engine mount, and tail attachments due to insufficient fatigue life or improper material/heat treatment.
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Required Actions
Replace specified bolts in fuselage to center wing, outer wing to center wing, vertical stabilizer to fuselage tail, engine mount to firewall, and horizontal stabilizer to fuselage tail attachments with NAS bolts (rolled threads after heat treatment) or special studs as specified. Scrappage of removed bolts is required.
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Compliance Time
At every 9,000 hours total airplane flight time, with possible extension up to 18,000 hours if specific stud replacements are made. Extensions beyond 9,000 hours require CAA Inspector approval, not exceeding 1,500 hours after January 26, 1948, and must align with regular overhaul periods.
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Affected Aircraft
Douglas C-54 and DC-4 aircraft models including C54-DC, C54A-DC, C54B-DC, C54D-DC, C54E-DC, C54G-DC, and DC-4, all serial numbers.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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