AD 82-10-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus Helicopters | AS355E | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters |
| aircraft | Airbus Helicopters | AS355F | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters |
| aircraft | Airbus Helicopters | AS350B | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters |
| aircraft | Airbus Helicopters | AS350C | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters |
| aircraft | Airbus Helicopters | AS350D | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters |
| aircraft | Airbus Helicopters | AS350D1 | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters |
Unsafe Condition
Bond failure between the tail rotor blade body and the stainless steel leading edge strip exceeding 10 percent of the strip bond area.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect tail rotor blades by tapping along the span and over the surface of the leading edge strip with a coin or similar device. Remove affected blades before further flight if a change in sound tone indicates bond failure exceeding 10 percent of the bond area.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight after the effective date of this AD, and thereafter at intervals not to exceed 10 hours' time in service from the last inspection until the tail rotor blades attain 100 hours' or more total time in service since new or since replacement of the stainless steel leading edge strip.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Societe Nationale Industrielle Aerospatiale (SNIAS) Model AS350 and AS355 Series helicopters equipped with tail rotor blades P/N 350A.12.0030.01, 02, 04, or 05.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Tail Rotor Blades
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_82-10-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-10-01 Document Type: AD Final Rules Docket Number: 82-ASW-16 Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 ...Show more Subject: Tail Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: 05/06/1982 Effective Date: 05/10/1982 Make: Airbus Helicopters Model: AS355E | AS355F | AS350B | AS350C | AS350D | AS350D1 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-730: International Validation Branch CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 82-10-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 82-ASW-16 AMENDMENT: 39-4373 AD NUMBER: 82-10-01 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters ACTION: SUMMARY: DATES: Effective May 10, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-10-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4373. Applies to Model AS350 and AS355 Series helicopters certificated in all categories that are equipped with tail rotor blades P/N 350A.12.0030.01, 02, 04, or 05 (Airworthiness Docket No. 82-ASW-16). Compliance required before further flight after the effective date of this AD, and thereafter at intervals not to exceed 10 hours' time in service from the last inspection until the tail rotor blades attain 100 hours' or more total time in service since new or since replacement of the stainless steel leading edge strip. To detect bond failure between each tail rotor blade body and the steel leading protective strip, inspect by tapping along the span and over the surface of the leading edge strip with a coin or similar device. Remove the affected tail rotor blade before further flight if a change in sound tone is found that indicates bond failure exceeds 10 percent of the strip bond area. Equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Aerospatiale Telex Service No. 2366 for all Model AS350 and AS355 operations dated February 4, 1982, pertains to this subject.) This amendment becomes effective May 10, 1982. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_82-10-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 82-10-01 Document Type: AD Final Rules Docket Number: 82-ASW-16 Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 ...Show more Subject: Tail Rotor Blades Status: Current Citation: This information is not available. Citation Publish Date: 05/06/1982 Effective Date: 05/10/1982 Make: Airbus Helicopters Model: AS355E | AS355F | AS350B | AS350C | AS350D | AS350D1 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-730: International Validation Branch CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 82-10-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 82-ASW-16 AMENDMENT: 39-4373 AD NUMBER: 82-10-01 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS350 and AS355 Series Helicopters ACTION: SUMMARY: DATES: Effective May 10, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 82-10-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4373. Applies to Model AS350 and AS355 Series helicopters certificated in all categories that are equipped with tail rotor blades P/N 350A.12.0030.01, 02, 04, or 05 (Airworthiness Docket No. 82-ASW-16). Compliance required before further flight after the effective date of this AD, and thereafter at intervals not to exceed 10 hours' time in service from the last inspection until the tail rotor blades attain 100 hours' or more total time in service since new or since replacement of the stainless steel leading edge strip. To detect bond failure between each tail rotor blade body and the steel leading protective strip, inspect by tapping along the span and over the surface of the leading edge strip with a coin or similar device. Remove the affected tail rotor blade before further flight if a change in sound tone is found that indicates bond failure exceeds 10 percent of the strip bond area. Equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Aerospatiale Telex Service No. 2366 for all Model AS350 and AS355 operations dated February 4, 1982, pertains to this subject.) This amendment becomes effective May 10, 1982. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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