AD 87-13-05 R1
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus Helicopters | AS355E | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters |
| aircraft | Airbus Helicopters | AS355F | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters |
| aircraft | Airbus Helicopters | AS355F1 | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters |
| aircraft | Airbus Helicopters | AS355F2 | Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters |
Unsafe Condition
Unbonding of main gearbox suspension bar end fittings, leading to possible cracking or protrusion of the PR compound and failure of the bars.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect suspension bars for bearing displacement, cracking, or PR compound protrusion within 10 hours time in service after the effective date. Affix adhesive tape around each bar end if no discrepancies found. Conduct subsequent visual tape checks every 10 hours time in service. Replace faulty bars with serviceable parts.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 10 hours time in service after the effective date of this AD
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Affected Aircraft
Societe Nationale Industrielle Aerospatiale (SNIAS) Model AS355E, AS355F, AS355F1, AS355F2 helicopters equipped with main gearbox suspension bars having Part Numbers 355A-38-0040-02, -03, -04, -05.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Components Fatigue Failure
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_87-13-05_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-13-05 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters Subject: Components Fatigue Failure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/08/1988 Make: Airbus Helicopters Model: AS355E | AS355F | AS355F1 | AS355F2 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 87-13-05 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5927 AD NUMBER: 87-13-05 R1 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters ACTION: SUMMARY: DATES: Effective June 8, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-13-05 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5651 as amended by Amendment 39-5927. Applies to Aerospatiale Model AS 355 series helicopters, certificated in any category which are equipped with main gearbox suspension bars with Part Numbers 355A-38-0040-02, -03, -04, -05. Compliance is required as indicated (unless already accomplished). To detect possible unbonding of main gearbox suspension bar end fittings and to prevent failure of the bars, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD: (1) Visually inspect the ends of each suspension bar for displacement of the spherical bearings relative to the tube and for cracking or protrusion of the PR compound as shown in figure No. 1. If this inspection is conducted without disassembly, use a light and inspection mirror as needed to inspect both ends of each bar. (2) If no bearing displacement or PR compound discrepancies are found, affix an adhesive tape such as POLYPENCO A 2007 around each end of each bar. Locate the edge of the tape nearest the end of the bar so that it is in line with (and tangent to) the surface of the anchoring lug as shown in figure No. 2. This will provide an aid for use in repetitive checks. (b) After the initial inspection of paragraph (a)(1) and modification of paragraph (a)(2), conduct a visual check of the marking tapes on the suspension bars thereafter at intervals not to exceed 10 hours time in service: (1) Check that the edge of the tape is in line with the anchoring lug surface as shown in Figure No. 2. This check may be conducted by the pilot. The person performing this check shall make appropriate entries of the results of the check in the aircraft records. (2) If the tape edge is no longer in line with the anchoring lug surface, remove the bar for a closer inspection for bearing displacement or PR compound protrusion as shown in figure No. 1. (c) Replace all bars found to be faulty with serviceable parts. (d) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Department of Transportation, Federal Aviation Administration, Fort Worth, Texas 76193-5100, or by the Manager, Brussels Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (e) In accordance with FAR 21.197 and 21.199, flight is permitted to a base where the inspections required by this AD may be accomplished. (f) Aerospatiale Service Bulletin No. 05.16 pertains to the inspections and checks of this AD. This amendment, 39-5927, amends Amendment 39-5651 (52 FR 24142; June 29, 1987), AD 87-13-05. This amendment, 39-5927, becomes effective June 8, 1988. AD 87-13-05 R1 FIGURE NO. 1 BASIC CHECK FOR END FITTING DISPLACEMENT AD 87-13-05 R1 UNSATISFACTORY (Tape displaced relative to lug fitting) FIGURE NO. 2 TAPE LOCATION CHECK FOR END FITTING DISPLACEMENT FOOTER:
Document Text
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AD Final Rules - DRS_87-13-05_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-13-05 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters Subject: Components Fatigue Failure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/08/1988 Make: Airbus Helicopters Model: AS355E | AS355F | AS355F1 | AS355F2 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 87-13-05 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5927 AD NUMBER: 87-13-05 R1 SUBJECT HEADING: Airworthiness Directives; SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS) Model AS 355 Series Helicopters ACTION: SUMMARY: DATES: Effective June 8, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-13-05 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5651 as amended by Amendment 39-5927. Applies to Aerospatiale Model AS 355 series helicopters, certificated in any category which are equipped with main gearbox suspension bars with Part Numbers 355A-38-0040-02, -03, -04, -05. Compliance is required as indicated (unless already accomplished). To detect possible unbonding of main gearbox suspension bar end fittings and to prevent failure of the bars, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD: (1) Visually inspect the ends of each suspension bar for displacement of the spherical bearings relative to the tube and for cracking or protrusion of the PR compound as shown in figure No. 1. If this inspection is conducted without disassembly, use a light and inspection mirror as needed to inspect both ends of each bar. (2) If no bearing displacement or PR compound discrepancies are found, affix an adhesive tape such as POLYPENCO A 2007 around each end of each bar. Locate the edge of the tape nearest the end of the bar so that it is in line with (and tangent to) the surface of the anchoring lug as shown in figure No. 2. This will provide an aid for use in repetitive checks. (b) After the initial inspection of paragraph (a)(1) and modification of paragraph (a)(2), conduct a visual check of the marking tapes on the suspension bars thereafter at intervals not to exceed 10 hours time in service: (1) Check that the edge of the tape is in line with the anchoring lug surface as shown in Figure No. 2. This check may be conducted by the pilot. The person performing this check shall make appropriate entries of the results of the check in the aircraft records. (2) If the tape edge is no longer in line with the anchoring lug surface, remove the bar for a closer inspection for bearing displacement or PR compound protrusion as shown in figure No. 1. (c) Replace all bars found to be faulty with serviceable parts. (d) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Department of Transportation, Federal Aviation Administration, Fort Worth, Texas 76193-5100, or by the Manager, Brussels Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (e) In accordance with FAR 21.197 and 21.199, flight is permitted to a base where the inspections required by this AD may be accomplished. (f) Aerospatiale Service Bulletin No. 05.16 pertains to the inspections and checks of this AD. This amendment, 39-5927, amends Amendment 39-5651 (52 FR 24142; June 29, 1987), AD 87-13-05. This amendment, 39-5927, becomes effective June 8, 1988. AD 87-13-05 R1 FIGURE NO. 1 BASIC CHECK FOR END FITTING DISPLACEMENT AD 87-13-05 R1 UNSATISFACTORY (Tape displaced relative to lug fitting) FIGURE NO. 2 TAPE LOCATION CHECK FOR END FITTING DISPLACEMENT FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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