AD 64-27-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Sud Aviation | Caravelle SE 210 Model VIR | Airworthiness Directives; SUD AVIATION Model SE 210 Caravelle VIR Aircraft |
Unsafe Condition
Fatigue failure of the main landing gear steel axle beams due to cracks around threaded holes.
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Required Actions
Visually inspect main landing gear steel axle beams (P/N 269028B and 269029B) for cracks around threaded holes as specified in Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34. Perform inspections with magnifying glass and fluorescent magnetic particle inspection as required. Rework holes per specified bulletin and replace cracked parts before flight.
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Compliance Time
Within 430 hours' time in service after January 1, 1965, and at intervals not exceeding 430 hours' time in service. Additional inspections required at 5,530 hours' total time in service or within 430 hours' total time in service based on existing hours. Rework required by 8,000 and 12,000 hours' total time in service.
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Affected Aircraft
SUD AVIATION Model SE 210 Caravelle VIR Aircraft with main landing gear steel axle beams P/N 269028B and 269029B.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear Beams
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-27-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-27-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SUD AVIATION Model SE 210 Caravelle VIR Aircraft Subject: Main Landing Gear Beams Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/01/1965 Make: Sud Aviation Model: Caravelle SE 210 Model VIR Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 64-27-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-8 AD NUMBER: 64-27-03 SUBJECT HEADING: Airworthiness Directives; SUD AVIATION Model SE 210 Caravelle VIR Aircraft ACTION: SUMMARY: DATES: Effective January 1, 1965. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-27-03 SUD AVIATION: Amdt. 39-8 Part 39 (New) Federal Register December 2, 1964. Applies to Model SE 210 Caravelle VIR Aircraft. Compliance required as indicated. In order to prevent fatigue failure of the main landing gear steel axle beams accomplish the following: (a) Within 430 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 430 hours' time in service from the last inspection, visually inspect all main landing gear steel axle beams, P/N's 269028B and 269029B, for cracks around threaded holes, as specified in Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963. (Note: This inspection may be made without disassembly of tubing support components.) (b) Within 860 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 860 hours' time in service from the last inspection, remove the lower tubing support shield and visually inspect with a magnifying glass the lower threaded holes in the main landing gear steel axle beams for cracks. (c) Unless previously accomplished remove the lower tubing support shielding and inspect for cracks all lower threaded holes in the main landing gear steel axle beams and surrounding areas using fluorescent magnetic particle inspection or FAA approved equivalent at the following times: (1) For landing gear with between 4,500 hours' and 5,100 hours' total time in service as of the effective date of this AD accomplish the inspection before the accumulation of 5,530 hours' total time in service. (2) For landing gear with 5,100 or more hours' total time in service as of the effective date of this AD accomplish the inspection within 430 hours' total time in service after the effective date of this AD. (d) Within 8,000 hours' total time in service rework all the lower threaded holes on axle beams as specified in Hispano Suiza Aero-service Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, or an FAA approved equivalent. The repetitive inspections specified in (b) and the inspection specified in (c) need not be performed after this rework has been accomplished. (e) Within 12,000 hours' total time in service rework in accordance with Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, or an FAA approved equivalent all holes in the landing gear which have not previously been reworked in accordance with (d). This AD no longer applies to aircraft on which this rework has been accomplished. (f) Replace any parts found cracked before further flight. (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Division, Paris, France, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, covers this same subject.) This directive effective January 1, 1965. FOOTER:
Document Text
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AD Final Rules - DRS_64-27-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-27-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SUD AVIATION Model SE 210 Caravelle VIR Aircraft Subject: Main Landing Gear Beams Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/01/1965 Make: Sud Aviation Model: 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: 64-27-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-8 AD NUMBER: 64-27-03 SUBJECT HEADING: Airworthiness Directives; SUD AVIATION Model SE 210 Caravelle VIR Aircraft ACTION: SUMMARY: DATES: Effective January 1, 1965. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-27-03 SUD AVIATION: Amdt. 39-8 Part 39 (New) Federal Register December 2, 1964. Applies to Model SE 210 Caravelle VIR Aircraft. Compliance required as indicated. In order to prevent fatigue failure of the main landing gear steel axle beams accomplish the following: (a) Within 430 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 430 hours' time in service from the last inspection, visually inspect all main landing gear steel axle beams, P/N's 269028B and 269029B, for cracks around threaded holes, as specified in Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963. (Note: This inspection may be made without disassembly of tubing support components.) (b) Within 860 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 860 hours' time in service from the last inspection, remove the lower tubing support shield and visually inspect with a magnifying glass the lower threaded holes in the main landing gear steel axle beams for cracks. (c) Unless previously accomplished remove the lower tubing support shielding and inspect for cracks all lower threaded holes in the main landing gear steel axle beams and surrounding areas using fluorescent magnetic particle inspection or FAA approved equivalent at the following times: (1) For landing gear with between 4,500 hours' and 5,100 hours' total time in service as of the effective date of this AD accomplish the inspection before the accumulation of 5,530 hours' total time in service. (2) For landing gear with 5,100 or more hours' total time in service as of the effective date of this AD accomplish the inspection within 430 hours' total time in service after the effective date of this AD. (d) Within 8,000 hours' total time in service rework all the lower threaded holes on axle beams as specified in Hispano Suiza Aero-service Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, or an FAA approved equivalent. The repetitive inspections specified in (b) and the inspection specified in (c) need not be performed after this rework has been accomplished. (e) Within 12,000 hours' total time in service rework in accordance with Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, or an FAA approved equivalent all holes in the landing gear which have not previously been reworked in accordance with (d). This AD no longer applies to aircraft on which this rework has been accomplished. (f) Replace any parts found cracked before further flight. (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Division, Paris, France, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, covers this same subject.) This directive effective January 1, 1965. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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