AD 82-19-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus Helicopters | SA330J | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model SA330J Series Helicopters |
Unsafe Condition
Cracks in the main rotor head outboard spindle lugs due to fretting corrosion could result in failure of the main rotor spindle, leading to loss of helicopter control.
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Required Actions
Inspect main rotor spindle lug bores for cracks using magnetic particle inspection within 10 hours' spindle time after AD effective date. Subsequent inspections with dye penetrant or equivalent are required within 750 hours' spindle time after each prior inspection. Install spindles with bushings per AMS 07.43.078 within 1,500 hours' spindle time or next overhaul. Replace cracked spindles before flight.
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Compliance Time
Within the next 10 hours' spindle time in service after the effective date of this AD
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Affected Aircraft
Societe Nationale Industrielle Aerospatiale (SNIAS) Model SA330J series helicopters equipped with main rotor spindles P/N 330A31.1122.03, 330A31.1122.06 to 330A31.1122.08.
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Federal Register Abstract
Main Rotor Spindles
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_82-19-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-19-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model SA330J Series Helicopters Subject: Main Rotor Spindles Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/27/1982 Make: Airbus Helicopters Model: SA330J Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 82-19-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4460 AD NUMBER: 82-19-03 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model SA330J Series Helicopters ACTION: SUMMARY: DATES: Effective September 27, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-19-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4460. Applies to Model SA330J series helicopters certificated in all categories that are equipped with main rotor spindles P/N 330A31.1122.03, 330A31.1122.06 to 330A31.1122.08. Compliance required as indicated. To detect possible cracks and to prevent fretting corrosion and possible cracking of the main rotor head outboard spindle lugs, accomplish the following: (a) Within the next 10 hours' spindle time in service after the effective date of this AD, unless already accomplished, remove the spindles from the helicopter and inspect each main rotor spindle lug bore for cracks using a magnetic particle inspection method. (b) Within 750 hours' spindle time in service after inspection per paragraph (a) of this AD, inspect each lug bore for cracks using a dye penetrant or equivalent inspection method. (c) Within 750 hours' spindle time in service after inspection per paragraph (b) of this AD, remove the spindle from the helicopter and inspect each lug bore for cracks using a magnetic particle inspection method. (d) Within 1,500 hours' spindle time in service after the effective date of this AD or at next overhaul of the main rotor head, whichever comes first, install spindles that have bushings installed in accordance with Aerospatiale Modification Instructions, AMS 07.43.078, or FAA approved equivalent. The inspections, paragraphs (b) and (c) of this AD, are not required after these bushings are installed. (e) Replace spindles having a cracked bore prior to further flight. Install serviceable spindles. (f) Alternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Aerospatiale Service Bulletin No. 01.35 pertains to visual inspections and protective finish of the spindle lug bore.) This amendment becomes effective September 27, 1982. FOOTER:
Document Text
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AD Final Rules - DRS_82-19-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-19-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model SA330J Series Helicopters Subject: Main Rotor Spindles Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/27/1982 Make: Airbus Helicopters Model: SA330J Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 82-19-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4460 AD NUMBER: 82-19-03 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model SA330J Series Helicopters ACTION: SUMMARY: DATES: Effective September 27, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-19-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4460. Applies to Model SA330J series helicopters certificated in all categories that are equipped with main rotor spindles P/N 330A31.1122.03, 330A31.1122.06 to 330A31.1122.08. Compliance required as indicated. To detect possible cracks and to prevent fretting corrosion and possible cracking of the main rotor head outboard spindle lugs, accomplish the following: (a) Within the next 10 hours' spindle time in service after the effective date of this AD, unless already accomplished, remove the spindles from the helicopter and inspect each main rotor spindle lug bore for cracks using a magnetic particle inspection method. (b) Within 750 hours' spindle time in service after inspection per paragraph (a) of this AD, inspect each lug bore for cracks using a dye penetrant or equivalent inspection method. (c) Within 750 hours' spindle time in service after inspection per paragraph (b) of this AD, remove the spindle from the helicopter and inspect each lug bore for cracks using a magnetic particle inspection method. (d) Within 1,500 hours' spindle time in service after the effective date of this AD or at next overhaul of the main rotor head, whichever comes first, install spindles that have bushings installed in accordance with Aerospatiale Modification Instructions, AMS 07.43.078, or FAA approved equivalent. The inspections, paragraphs (b) and (c) of this AD, are not required after these bushings are installed. (e) Replace spindles having a cracked bore prior to further flight. Install serviceable spindles. (f) Alternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Aerospatiale Service Bulletin No. 01.35 pertains to visual inspections and protective finish of the spindle lug bore.) This amendment becomes effective September 27, 1982. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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