AD 83-24-10 R1
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | BAC 1-11 200 Series | Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes |
| aircraft | Airbus SAS | BAC 1-11 400 Series | Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes |
Unsafe Condition
Cracking and corrosion of the fuselage pressure vessel in the lower fuselage skin areas between stations 416-456 and 630-690, and stringers 32(LH) and 32(RH), which could lead to structural failure and cabin depressurization.
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Required Actions
Visually inspect the interior of the lower fuselage skin between stations 416-456 and 630-690 and stringers 32(LH) and 32(RH) for corrosion and cracks, ensure drain paths are unobstructed, and follow British Aerospace Alert Service Bulletin 53-A-PM5632. For airplanes with long range fuel tanks or water injection tanks, follow paragraph 2.1.3 of the service bulletin. If cracks or corrosion are found, rework or repair using Structural Repair Manual chapters 53-01-0 or 53-02-0 before further flight and continue inspections at specified intervals.
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Compliance Time
Within the next 12 months after the effective date of this AD, unless accomplished within the last 2 years, and thereafter at intervals not to exceed 3 years from the last inspection.
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Affected Aircraft
British Aerospace Model BAC 1-11 200 and 400 series airplanes, certificated in all categories.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Lower Fuselage Skin
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_83-24-10_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-24-10 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes Subject: Lower Fuselage Skin Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/04/1985 Make: Airbus SAS Model: BAC 1-11 200 Series | BAC 1-11 400 Series Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 83-24-10 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5053 AD NUMBER: 83-24-10 R1 SUBJECT HEADING: Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes ACTION: SUMMARY: DATES: Effective June 4, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-24-10 R1 BRITISH AEROSPACE: Amendment 39-4780 as amended by Amendment 39- 5053. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated unless already accomplished. To detect cracking and corrosion and to prevent structural failure of the fuselage pressure vessel with the resultant cabin depressurization, accomplish the following: A. Within the next 12 months after the effective date of this AD, unless accomplished within the last 2 years, and thereafter at intervals not to exceed 3 years from the last inspection, visually inspect for corrosion and cracks the interior of the lower fuselage skin between stations 416-456 and stringers 32(LH) and 32(RH) and the interior of the lower fuselage skin between stations 630-690 and stringers 32(LH) and 32(RH), and ensure that drain paths in these areas are unobstructed, in accordance with paragraphs 2.1.1 and 2.1.2 of British Aerospace Alert Service Bulletin 53-A-PM5632, dated August 18, 1978. B. On airplanes having long range fuel tanks or water injection tanks installed, accomplish the instructions of paragraph 2.1.3 of the service bulletin. C. If cracks or corrosion are found during any inspection required by this AD, before further flight, rework or repair in accordance with Structural Repair Manual, Chapters 53-01-0 or 53-02-0 as appropriate, and continue the repetitive inspections at the intervals specified in paragraph A. of this AD. 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. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. Amendment 39-4780 became effective January 15, 1984. This Amendment 39-5053 becomes effective June 4, 1985. FOOTER:
Document Text
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AD Final Rules - DRS_83-24-10_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-24-10 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes Subject: Lower Fuselage Skin Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/04/1985 Make: Airbus SAS Model: BAC 1-11 200 Series | BAC 1-11 400 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: 83-24-10 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5053 AD NUMBER: 83-24-10 R1 SUBJECT HEADING: Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes ACTION: SUMMARY: DATES: Effective June 4, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-24-10 R1 BRITISH AEROSPACE: Amendment 39-4780 as amended by Amendment 39- 5053. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated unless already accomplished. To detect cracking and corrosion and to prevent structural failure of the fuselage pressure vessel with the resultant cabin depressurization, accomplish the following: A. Within the next 12 months after the effective date of this AD, unless accomplished within the last 2 years, and thereafter at intervals not to exceed 3 years from the last inspection, visually inspect for corrosion and cracks the interior of the lower fuselage skin between stations 416-456 and stringers 32(LH) and 32(RH) and the interior of the lower fuselage skin between stations 630-690 and stringers 32(LH) and 32(RH), and ensure that drain paths in these areas are unobstructed, in accordance with paragraphs 2.1.1 and 2.1.2 of British Aerospace Alert Service Bulletin 53-A-PM5632, dated August 18, 1978. B. On airplanes having long range fuel tanks or water injection tanks installed, accomplish the instructions of paragraph 2.1.3 of the service bulletin. C. If cracks or corrosion are found during any inspection required by this AD, before further flight, rework or repair in accordance with Structural Repair Manual, Chapters 53-01-0 or 53-02-0 as appropriate, and continue the repetitive inspections at the intervals specified in paragraph A. of this AD. 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. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. Amendment 39-4780 became effective January 15, 1984. This Amendment 39-5053 becomes effective June 4, 1985. FOOTER:
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Retrieved: Apr 8, 2026
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