AD 82-24-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 707-100 Long Body | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 707-100B Long Body | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 707-100B Short Body | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 707-200 | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 707-300 Series | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 707-300B Series | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 707-300C Series | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 707-400 Series | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 720 Series | BOEING Model 707/720 Series Airplanes |
| aircraft | The Boeing Company | 720B Series | BOEING Model 707/720 Series Airplanes |
Unsafe Condition
Cracks in the nacelle strut diagonal brace and associated fittings due to fatigue.
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Required Actions
Inspect nacelle strut diagonal braces and associated fittings within 500 landings after the effective date using Boeing Service Bulletin A3364, Rev. 3, NSC2 or later FAA-approved revisions. Repeat inspections at intervals specified in Tables 1, 2, and 3. Replace cracked parts or those oversized beyond limits before further flight. For Group III, IV, and VI airplanes, replace diagonal brace assembly if outboard diagonal brace end fitting attach holes are oversized beyond limits within 1000 landings since oversizing.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 500 landings after the effective date
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Affected Aircraft
Boeing Model 707/720 series airplanes listed in Boeing Service Bulletin A3364, Revision 3, NSC-2 and later FAA approved revisions with nacelle strut diagonal braces and associated fittings that have accumulated 7500 or more landings.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Nacelle Strut Diagonal Braces
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_82-24-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-24-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 707/720 Series Airplanes Subject: Nacelle Strut Diagonal Braces Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/23/1982 Make: The Boeing Company Model: 707-100 Long Body | 707-100B Long Body | 707-100B Short Body | 707-200 | 707-300 Series | 707-300B S...Show more 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: 82-24-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4496 AD NUMBER: 82-24-03 SUBJECT HEADING: BOEING Model 707/720 Series Airplanes ACTION: SUMMARY: DATES: Effective November 23, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-24-03 BOEING: Amendment 39-4496. Applies to all Model 707/720 series airplanes listed in Boeing Service Bulletin A3364, Revision 3, NSC-2 and later FAA approved revisions with nacelle strut diagonal braces and associated fittings which have accumulated 7500 or more landings. To detect cracks in the nacelle strut diagonal brace and associated fittings accomplish the following: A. Within 500 landings after the effective date of this AD unless already accomplished, inspect the nacelle strut diagonal braces and associated fittings in accordance with Boeing Service Bulletin A3364, Rev. 3, NSC2 or later FAA-approved revisions, and repeat thereafter at the intervals specified in Tables 1, 2, and 3 below. B. If cracks are found, replace the cracked part prior to further flight or repair in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. Parts oversized beyond the limits specified in Boeing Service Bulletin A3364 must be replaced prior to further flight. C. For Group III, IV, and VI airplanes, as specified in the service bulletin, replace the diagonal brace assembly if the outboard diagonal brace end fitting (forward or aft) attach holes have been oversized beyond the limits specified in Boeing Service Bulletin A3364, Rev. 3 or later FAA-approved revisions within 1000 landings since oversizing. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. TABLE I Forward Mating Fitting Type Inspection Repeat Intervals Not To Exceed Landings Visual 250 Hi frequency 7500 Hi frequency followed by shot peening 12000 TABLE II Aft Mating Fitting Type Inspection Repeat Intervals Not To Exceed Landings Visual 250 1. Hi frequency or dye penetrant of web. 7500 2. Hi frequency of lug hole with bushing removed and hole oversized. 1. Hi frequency of lug hole with bushing removed, oversizing and peening of lug hole surface. 12000 2. Hi frequency or dye penetrant of web and preening of web. TABLE III Diagonal Brace Assembly Type Inspection Repeat Intervals Not To Exceed Landings Hi frequency Interior only 2500 Hi frequency Exterior (fitting removal) with hole oversizing. 7500 Hi frequency Exterior with hole oversizing and peening 12000 Hi frequency Exterior with holes previously oversized to limit and peening. 7500 NOTE: Hole oversizing cannot exceed limits specified in Service Bulletin. The manufacturer's specification 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 may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at the FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 80-14-14. This amendment becomes effective November 23, 1982. FOOTER:
Document Text
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AD Final Rules - DRS_82-24-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-24-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: BOEING Model 707/720 Series Airplanes Subject: Nacelle Strut Diagonal Braces Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/23/1982 Make: The Boeing Company Model: 707-100 Long Body | 707-100B Long Body | 707-100B Short Body | 707-200 | 707-300 Series | 707-300B S...Show more 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: 82-24-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4496 AD NUMBER: 82-24-03 SUBJECT HEADING: BOEING Model 707/720 Series Airplanes ACTION: SUMMARY: DATES: Effective November 23, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-24-03 BOEING: Amendment 39-4496. Applies to all Model 707/720 series airplanes listed in Boeing Service Bulletin A3364, Revision 3, NSC-2 and later FAA approved revisions with nacelle strut diagonal braces and associated fittings which have accumulated 7500 or more landings. To detect cracks in the nacelle strut diagonal brace and associated fittings accomplish the following: A. Within 500 landings after the effective date of this AD unless already accomplished, inspect the nacelle strut diagonal braces and associated fittings in accordance with Boeing Service Bulletin A3364, Rev. 3, NSC2 or later FAA-approved revisions, and repeat thereafter at the intervals specified in Tables 1, 2, and 3 below. B. If cracks are found, replace the cracked part prior to further flight or repair in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. Parts oversized beyond the limits specified in Boeing Service Bulletin A3364 must be replaced prior to further flight. C. For Group III, IV, and VI airplanes, as specified in the service bulletin, replace the diagonal brace assembly if the outboard diagonal brace end fitting (forward or aft) attach holes have been oversized beyond the limits specified in Boeing Service Bulletin A3364, Rev. 3 or later FAA-approved revisions within 1000 landings since oversizing. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. TABLE I Forward Mating Fitting Type Inspection Repeat Intervals Not To Exceed Landings Visual 250 Hi frequency 7500 Hi frequency followed by shot peening 12000 TABLE II Aft Mating Fitting Type Inspection Repeat Intervals Not To Exceed Landings Visual 250 1. Hi frequency or dye penetrant of web. 7500 2. Hi frequency of lug hole with bushing removed and hole oversized. 1. Hi frequency of lug hole with bushing removed, oversizing and peening of lug hole surface. 12000 2. Hi frequency or dye penetrant of web and preening of web. TABLE III Diagonal Brace Assembly Type Inspection Repeat Intervals Not To Exceed Landings Hi frequency Interior only 2500 Hi frequency Exterior (fitting removal) with hole oversizing. 7500 Hi frequency Exterior with hole oversizing and peening 12000 Hi frequency Exterior with holes previously oversized to limit and peening. 7500 NOTE: Hole oversizing cannot exceed limits specified in Service Bulletin. The manufacturer's specification 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 may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at the FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 80-14-14. This amendment becomes effective November 23, 1982. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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