AD 83-05-06
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Sud Aviation | Caravelle SE 210 Model III | Airworthiness Directives; AEROSPATIALE Model Caravelle SE-210 III and VIR Airplanes |
| aircraft | Sud Aviation | Caravelle SE 210 Model VIR | Airworthiness Directives; AEROSPATIALE Model Caravelle SE-210 III and VIR Airplanes |
Unsafe Condition
Structural failures due to corrosion, ovalization, or cracks in lower wing center junction fitting bores and main landing gear hinge shaft screws.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace main landing gear hinge shaft screws with specified parts within 500 landings. Inspect screws and lower wing center junction fitting bores for corrosion, ovalization, or cracks at intervals not exceeding 5,000 landings or 10,500/4,000 hours time in service. Inspect wing rib 44 upper cap fittings within 200 landings and reinspect at intervals not exceeding 2,000 landings, or 1,000 landings if cracks are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 500 landings or specified total landings/hours, as detailed in the AD, after the effective date (April 11, 1983).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
AEROSPATIALE (formerly SUD) Caravelle SE 210 Models III and VIR airplanes, all serial numbers.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Structural Inspection
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_83-05-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-05-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; AEROSPATIALE Model Caravelle SE-210 III and VIR Airplanes Subject: Structural Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/11/1983 Make: Sud Aviation Model: Caravelle SE 210 Model III | Caravelle SE 210 Model VIR Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 83-05-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4579 AD NUMBER: 83-05-06 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model Caravelle SE-210 III and VIR Airplanes ACTION: SUMMARY: DATES: Effective April 11, 1983. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-05-06 AEROSPATIALE (formerly SUD): Amendment 39-4579. Applies to all Caravelle SE-210 Models III and VIR airplanes, certificated in all categories. 1. To prevent structural failures, accomplish the following within the time in service or number of flights specified in each paragraph below after the effective date of this AD, unless already accomplished. A. Compliance required in accordance with SUD Service Bulletin 32-86, Revision 7, and/or in accordance with SUD Service Bulletin 32-106, Revision 4, as noted; (1) Replace P/N 210.41.10.011-01 main landing gear hinge shaft aft end screws with P/N 210.41.10.100-01 screws (Service Bulletin 32-86) or with P/N 210.41.10.652-01 screws and 210.41.10.648-01 plugs (Service Bulletin 32-106) within the next 500 landings. (2) Inspect P/N 210.41.10.100-01 screws in accordance with Service Bulletin 32-86 within the next 500 landings or within 8,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings. (3) Inspect P/N 210.41.10.652-01 screws in accordance with Service Bulletin 32-106 within the next 500 landings or within 10,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings. B. Compliance required in accordance with SUD Service Bulletin No. 57-40, Revision 10; (1) Inspect the lower wing center junction fitting I3 and I5 bores for corrosion, ovalization, or cracks within the next 200 hours time in service or within 15,000 hours total time in service, whichever occurs later, and thereafter at intervals not to exceed 10,500 hours time in service for airplanes with a maximum takeoff weight of 52 tons or less and 4,000 hours time in service for airplanes with a maximum takeoff weight of over 52 tons. (2) Inspect the lower wing center junction fitting I1, I2, and I4 bores for corrosion, ovalization, or cracks within the next 200 hours time in service or within 18,000 hours total time service, whichever occurs later, and thereafter at intervals not to exceed 8,000 hours time in service. (3) Repair or replace fittings per the service bulletin instructions. C. Inspect wing rib 44 upper cap fittings within the next 200 landings in accordance with SUD Service Bulletin 57-47, Revision 6. If no cracks are found, reinspect at intervals not to exceed 2,000 landings thereafter. If cracks are found, repair as necessary per the service bulletin and reinspect at intervals not to exceed 1,000 landings thereafter. 2. 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. 3. 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. 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). This amendment becomes effective April 11, 1983. FOOTER:
Document Text
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AD Final Rules - DRS_83-05-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-05-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; AEROSPATIALE Model Caravelle SE-210 III and VIR Airplanes Subject: Structural Inspection Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/11/1983 Make: Sud Aviation Model: Caravelle SE 210 Model III | Caravelle SE 210 Model VIR 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: 83-05-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4579 AD NUMBER: 83-05-06 SUBJECT HEADING: Airworthiness Directives; AEROSPATIALE Model Caravelle SE-210 III and VIR Airplanes ACTION: SUMMARY: DATES: Effective April 11, 1983. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-05-06 AEROSPATIALE (formerly SUD): Amendment 39-4579. Applies to all Caravelle SE-210 Models III and VIR airplanes, certificated in all categories. 1. To prevent structural failures, accomplish the following within the time in service or number of flights specified in each paragraph below after the effective date of this AD, unless already accomplished. A. Compliance required in accordance with SUD Service Bulletin 32-86, Revision 7, and/or in accordance with SUD Service Bulletin 32-106, Revision 4, as noted; (1) Replace P/N 210.41.10.011-01 main landing gear hinge shaft aft end screws with P/N 210.41.10.100-01 screws (Service Bulletin 32-86) or with P/N 210.41.10.652-01 screws and 210.41.10.648-01 plugs (Service Bulletin 32-106) within the next 500 landings. (2) Inspect P/N 210.41.10.100-01 screws in accordance with Service Bulletin 32-86 within the next 500 landings or within 8,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings. (3) Inspect P/N 210.41.10.652-01 screws in accordance with Service Bulletin 32-106 within the next 500 landings or within 10,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings. B. Compliance required in accordance with SUD Service Bulletin No. 57-40, Revision 10; (1) Inspect the lower wing center junction fitting I3 and I5 bores for corrosion, ovalization, or cracks within the next 200 hours time in service or within 15,000 hours total time in service, whichever occurs later, and thereafter at intervals not to exceed 10,500 hours time in service for airplanes with a maximum takeoff weight of 52 tons or less and 4,000 hours time in service for airplanes with a maximum takeoff weight of over 52 tons. (2) Inspect the lower wing center junction fitting I1, I2, and I4 bores for corrosion, ovalization, or cracks within the next 200 hours time in service or within 18,000 hours total time service, whichever occurs later, and thereafter at intervals not to exceed 8,000 hours time in service. (3) Repair or replace fittings per the service bulletin instructions. C. Inspect wing rib 44 upper cap fittings within the next 200 landings in accordance with SUD Service Bulletin 57-47, Revision 6. If no cracks are found, reinspect at intervals not to exceed 2,000 landings thereafter. If cracks are found, repair as necessary per the service bulletin and reinspect at intervals not to exceed 1,000 landings thereafter. 2. 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. 3. 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. 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). This amendment becomes effective April 11, 1983. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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