AD 75-24-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 707-300 Series | BOEING Model 707-300, -300B, -300C and -400 Series Airplanes |
| aircraft | The Boeing Company | 707-300B Series | BOEING Model 707-300, -300B, -300C and -400 Series Airplanes |
| aircraft | The Boeing Company | 707-300C Series | BOEING Model 707-300, -300B, -300C and -400 Series Airplanes |
| aircraft | The Boeing Company | 707-400 Series | BOEING Model 707-300, -300B, -300C and -400 Series Airplanes |
Unsafe Condition
Cracks in the upper wing skin splice plate at W. S. 360.
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Required Actions
Conduct a low frequency eddy current inspection in accordance with Boeing Field Service Message M-7010-1256, or remove aerodynamic sealant between upper wing skins at W. S. 360 and visually inspect for cracks in the splice plate. Repairs must follow Boeing Service Bulletin No. 2510, Revision 3 or an approved method if cracks are found.
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Compliance Time
within the next 50 landings
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Affected Aircraft
Boeing 707-300, -300B, -300C, and -400 series airplanes with specific landing counts: 13,000+ landings for 707-300/-400; 11,000+ for 707-300B; 8,000+ for 707-300C, as listed in Boeing Service Bulletin No. 3157 Revision 3.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Upper Wing Skin Splice Plate
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_75-24-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-24-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 707-300, -300B, -300C and -400 Series Airplanes Subject: Upper Wing Skin Splice Plate Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: The Boeing Company Model: 707-300 Series | 707-300B Series | 707-300C Series | 707-400 Series Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 75-24-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2424 AD NUMBER: 75-24-01 SUBJECT HEADING: BOEING Model 707-300, -300B, -300C and -400 Series Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-24-01 BOEING: Amendment 39-2424. Applies to all Boeing 707-300, and -400 series airplanes with 13,000 or more landings; all 707-300B airplanes with 11,000 or more landings; and all 707-300C series airplanes with 8,000 or more landings, listed in Boeing Service Bulletin No. 3157 Revision 3, certificated in all categories. Compliance required as indicated. To detect cracks in the upper wing skin splice plate at W. S. 360, within the next 50 landings: (1) Conduct the low frequency eddy current inspection in accordance with Boeing Field Service Message M-7010-1256, dated October 9, 1975, unless already accomplished, or (2) Remove the aerodynamic sealant between the upper wing skins at W. S. 360 from the front spar to the rear spar and visually inspect for a crack in the splice plate, unless accomplished since October 3, 1975. If cracks are found, repair in accordance with Boeing Service Bulletin No. 2510, Revision 3, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Northwest Region. This is a one-time inspection. AD 75-03-01 (Amendment 39-2074) will be amended to provide for inspections similar to those provided herein. Telegraphic AD on this subject on October 15, 1975, is hereby superseded. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated October 17, 1975. FOOTER:
Document Text
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AD Final Rules - DRS_75-24-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-24-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 707-300, -300B, -300C and -400 Series Airplanes Subject: Upper Wing Skin Splice Plate Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: The Boeing Company Model: 707-300 Series | 707-300B Series | 707-300C Series | 707-400 Series 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: 75-24-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2424 AD NUMBER: 75-24-01 SUBJECT HEADING: BOEING Model 707-300, -300B, -300C and -400 Series Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-24-01 BOEING: Amendment 39-2424. Applies to all Boeing 707-300, and -400 series airplanes with 13,000 or more landings; all 707-300B airplanes with 11,000 or more landings; and all 707-300C series airplanes with 8,000 or more landings, listed in Boeing Service Bulletin No. 3157 Revision 3, certificated in all categories. Compliance required as indicated. To detect cracks in the upper wing skin splice plate at W. S. 360, within the next 50 landings: (1) Conduct the low frequency eddy current inspection in accordance with Boeing Field Service Message M-7010-1256, dated October 9, 1975, unless already accomplished, or (2) Remove the aerodynamic sealant between the upper wing skins at W. S. 360 from the front spar to the rear spar and visually inspect for a crack in the splice plate, unless accomplished since October 3, 1975. If cracks are found, repair in accordance with Boeing Service Bulletin No. 2510, Revision 3, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Northwest Region. This is a one-time inspection. AD 75-03-01 (Amendment 39-2074) will be amended to provide for inspections similar to those provided herein. Telegraphic AD on this subject on October 15, 1975, is hereby superseded. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated October 17, 1975. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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