AD 49-06-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-6 | DOUGLAS DC-6 Aircraft |
| aircraft | The Boeing Company | DC-6A | DOUGLAS DC-6 Aircraft |
| aircraft | The Boeing Company | DC-6B | DOUGLAS DC-6 Aircraft |
Unsafe Condition
Attachment bolts (fuselage to center wing, outer wing to center wing, vertical stabilizer to fuselage, horizontal stabilizer to fuselage, and engine mount to firewall) may fail due to fatigue or corrosion, leading to structural failure.
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Required Actions
Replace specified attachment bolts with approved replacements and scrap removed bolts. Use studs 2361992, 2361993, 4361995, and 4361994 (marked 'R') and NAS bolts with threads rolled after heat treatment for extended inspection intervals.
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Compliance Time
at every 8,000 hours of total flight time
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Affected Aircraft
The Boeing Company DC-6, DC-6A, DC-6B aircraft
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Federal Register Abstract
Attachment Bolts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_49-06-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 49-06-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: DOUGLAS DC-6 Aircraft Subject: Attachment Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: The Boeing Company Model: DC-6 | DC-6A | DC-6B Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 49-06-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 49-06-02 SUBJECT HEADING: DOUGLAS DC-6 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 49-06-02 DOUGLAS: Applies to DC-6 Aircraft. To be accomplished at every 8,000 hours of total flight time. Replace the following attachment bolts: (1) fuselage to center wing, (2) outer wing to center wing, (3) vertical stabilizer to fuselage, (4) horizontal stabilizer to fuselage and, (5) engine mount to firewall. The 8,000-hour period may be extended to 16,000 hours when studs 2325933 or 2340697, 2353832, 4329243 and 4333164 are replaced with studs 2361992, 2361993, 4361995 and 4361994, respectively, having letter "R" stamped on thread end and bolts in all other attachments listed are placed with NAS bolts with threads rolled after heat treatment. Bolts and studs removed from the airplane are to be scrapped and are not to be used again. (Douglas Service Bulletin DC-6 No. 410 contains a list of all studs and bolts affected and their replacements.) FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_49-06-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 49-06-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: DOUGLAS DC-6 Aircraft Subject: Attachment Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: The Boeing Company Model: DC-6 | DC-6A | DC-6B Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 49-06-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 49-06-02 SUBJECT HEADING: DOUGLAS DC-6 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 49-06-02 DOUGLAS: Applies to DC-6 Aircraft. To be accomplished at every 8,000 hours of total flight time. Replace the following attachment bolts: (1) fuselage to center wing, (2) outer wing to center wing, (3) vertical stabilizer to fuselage, (4) horizontal stabilizer to fuselage and, (5) engine mount to firewall. The 8,000-hour period may be extended to 16,000 hours when studs 2325933 or 2340697, 2353832, 4329243 and 4333164 are replaced with studs 2361992, 2361993, 4361995 and 4361994, respectively, having letter "R" stamped on thread end and bolts in all other attachments listed are placed with NAS bolts with threads rolled after heat treatment. Bolts and studs removed from the airplane are to be scrapped and are not to be used again. (Douglas Service Bulletin DC-6 No. 410 contains a list of all studs and bolts affected and their replacements.) FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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