AD 90-08-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Sud Aviation | Caravelle SE 210 Model III | Airworthiness Directives; SUD-SERVICE (FORMERLY SUD AVIATION) Caravelle SE 210 Model III and VIR Series Airplanes |
| aircraft | Sud Aviation | Caravelle SE 210 Model VIR | Airworthiness Directives; SUD-SERVICE (FORMERLY SUD AVIATION) Caravelle SE 210 Model III and VIR Series Airplanes |
Unsafe Condition
Fatigue cracks in the nose landing gear well angles could result in reduction of the structural integrity within that area of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform inspections (visual, dye penetrant, X-ray, or low frequency eddy current) of specific components (doublers, fuselage skin, skin panels, front angles) at frames 9, 15, and 17 in accordance with Sud-Service Service Bulletin 53-49, Revision 3. Repeat inspections at intervals not exceeding 2,500 or 5,000 landings as specified. Repair cracks prior to further flight per the service bulletin.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 32,500 landings or within 30 days after the effective date of this AD (May 4, 1990), whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Sud-Service Caravelle SE 210 Model III and VIR series airplanes, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Nose Landing Gear Well
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_90-08-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-08-02 Document Type: AD Final Rules Docket Number: 89-NM-247-AD Subject Heading: Airworthiness Directives; SUD-SERVICE (FORMERLY SUD AVIATION) Caravelle SE 210 Model III and VIR Ser...Show more Subject: Nose Landing Gear Well Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/04/1990 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SE 210 Model III | Caravelle SE 210 Model VIR Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 90-08-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-NM-247-AD AMENDMENT: 39-6558 AD NUMBER: 90-08-02 SUBJECT HEADING: Airworthiness Directives; SUD-SERVICE (FORMERLY SUD AVIATION) Caravelle SE 210 Model III and VIR Series Airplanes ACTION: SUMMARY: DATES: Effective May 4, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-08-02 SUD-SERVICE (FORMERLY SUD AVIATION): Amendment 39-6558. Docket No. 89-NM-247-AD. Applicability: All Sud-Service Caravelle SE 210 Model III and VIR series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To identify and correct fatigue cracks in the nose landing gear well angles, which could result in reduction of the structural integrity within that area of the airplane, accomplish the following: A. Prior to the accumulation of 32,500 landings or within 30 days after the effective date of this AD, whichever occurs later, perform the following inspections in accordance with Sud-Service Service Bulletin 53-49, Revision 3, dated June 2, 1986: 1. Perform a visual and dye penetrant inspection of doublers and fuselage skin bordering doublers (fitted in accordance with Sud-Service Service Bulletins 53-15 and 53-36) at frame 9 and frame 17, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings. 2. Perform an X-ray inspection or low frequency eddy current inspection of skin panels under doublers at frame 9 and at frame 17, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 5,000 landings. 3. Perform a visual inspection and dye penetrant inspection of the front angles at frame 15 on airplanes not fitted with doublers in this area, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings. 4. Perform an X-ray inspection of the front angles at frame 15, on airplanes fitted with repair doublers, in accordance with the service bulletin. Repeat this inspection at intervals not to exceed 5,000 landings. B. If cracks are found, repair prior to further flight, in accordance with Sud-Service Service Bulletin 53-49, Revision 3, dated June 2, 1986. Repeat inspections thereafter at intervals specified in paragraph A., above. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Rue de Bayonne, 31060 Toulouse Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6558, AD 90-08-02)) becomes effective on May 4, 1990. FOOTER:
Document Text
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AD Final Rules - DRS_90-08-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-08-02 Document Type: AD Final Rules Docket Number: 89-NM-247-AD Subject Heading: Airworthiness Directives; SUD-SERVICE (FORMERLY SUD AVIATION) Caravelle SE 210 Model III and VIR Ser...Show more Subject: Nose Landing Gear Well Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/04/1990 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: 90-08-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-NM-247-AD AMENDMENT: 39-6558 AD NUMBER: 90-08-02 SUBJECT HEADING: Airworthiness Directives; SUD-SERVICE (FORMERLY SUD AVIATION) Caravelle SE 210 Model III and VIR Series Airplanes ACTION: SUMMARY: DATES: Effective May 4, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-08-02 SUD-SERVICE (FORMERLY SUD AVIATION): Amendment 39-6558. Docket No. 89-NM-247-AD. Applicability: All Sud-Service Caravelle SE 210 Model III and VIR series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To identify and correct fatigue cracks in the nose landing gear well angles, which could result in reduction of the structural integrity within that area of the airplane, accomplish the following: A. Prior to the accumulation of 32,500 landings or within 30 days after the effective date of this AD, whichever occurs later, perform the following inspections in accordance with Sud-Service Service Bulletin 53-49, Revision 3, dated June 2, 1986: 1. Perform a visual and dye penetrant inspection of doublers and fuselage skin bordering doublers (fitted in accordance with Sud-Service Service Bulletins 53-15 and 53-36) at frame 9 and frame 17, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings. 2. Perform an X-ray inspection or low frequency eddy current inspection of skin panels under doublers at frame 9 and at frame 17, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 5,000 landings. 3. Perform a visual inspection and dye penetrant inspection of the front angles at frame 15 on airplanes not fitted with doublers in this area, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings. 4. Perform an X-ray inspection of the front angles at frame 15, on airplanes fitted with repair doublers, in accordance with the service bulletin. Repeat this inspection at intervals not to exceed 5,000 landings. B. If cracks are found, repair prior to further flight, in accordance with Sud-Service Service Bulletin 53-49, Revision 3, dated June 2, 1986. Repeat inspections thereafter at intervals specified in paragraph A., above. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Rue de Bayonne, 31060 Toulouse Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6558, AD 90-08-02)) becomes effective on May 4, 1990. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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