AD 64-02-06 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Sikorsky Aircraft Corporation | S-58A | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58B | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58BT | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58C | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58D | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58DT | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58E | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58ET | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58F | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58FT | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58G | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58H | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58HT | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58J | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S-58JT | Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters |
Unsafe Condition
Fatigue cracks have been found in the area of the rear three bolt holes of upper pylon folding hinge fitting P/N S1620-63130-2, the forward bolt holes of mating fitting P/N S1620-64127, the forward bolt hole of the lower pylon hinge fitting P/N S1620-64131, and the lug through which the hinge bolt passes of fittings P/N's S1620-64127 and S1620-64127-7.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct daily visual inspections of the area around the fitting bolt holes for cracks and replace any cracked fittings before further flight. Remove bushings, rework and inspect the bore of each hole, and install oversized replacement bushings P/N S1620-63129-7 within 100 hours' time in service after the effective date, depending on the fitting's time in service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 100 hours' time in service after the effective date of this AD
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
All Sikorsky Model S-58 series helicopters including models S-58A, S-58B, S-58BT, S-58C, S-58D, S-58DT, S-58E, S-58ET, S-58F, S-58FT, S-58G, S-58H, and others in the series.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Pylon and Tail Cone Fittings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-02-06_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-02-06 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters Subject: Pylon and Tail Cone Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/27/1988 Make: Sikorsky Aircraft Corporation Model: S-58A | S-58B | S-58BT | S-58C | S-58D | S-58DT | S-58E | S-58ET | S-58F | S-58FT | S-58G | S-58H | ...Show more 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: 64-02-06 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6090 AD NUMBER: 64-02-06 R1 SUBJECT HEADING: Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters ACTION: SUMMARY: DATES: Effective December 27, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-02-06 R1 SIKORSKY AIRCRAFT: Amendment 674 as amended by Amendment 39-6090. Applies to all Sikorsky Model S-58 series helicopters. Compliance is required as indicated unless already accomplished. Fatigue cracks have been found in the area of the rear three bolt holes of upper pylon folding hinge fitting P/N S1620-63130-2, the forward bolt holes of mating fitting P/N S1620-64127, the forward bolt hole of the lower pylon hinge fitting P/N S1620-64131, and the lug through which the hinge bolt passes of fittings P/N's S1620-64127 and S1620-64127-7. In order to preclude propagation of fatigue cracks in these areas and subsequent serious weakening of the pylon attachment, accomplish the following: (a) As of the effective date of this AD, conduct daily visual inspections of the area around the fitting bolt holes of all pylon and tail cone folding hinge fittings for cracks. Replace any cracked fittings before further flight. (b) Unless already accomplished, accomplish the following in accordance with Sikorsky Service Bulletin No. 58B20-11A within 100 hours' time in service after the effective date of this AD on all upper pylon hinge fittings P/N S1620-64127 with 1,900 hours' or more time in service, or prior to the accumulation of 2,000 hours' time in service on all fittings having less than 1,900 hours' time in service as of the effective date of this AD: (1) Remove all bushings from the hinges. (2) Rework and inspect the bore of each hole. (3) Install oversized replacement bushings P/N S1620-63129-7. (c) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, Aircraft Certification Service, ASW-110, FAA, Fort Worth, Texas 76193-0110. (d) In accordance with Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished. Airworthiness Directive 63-09-02 was superseded by AD 64-02-06 (Amendment 674; 29 FR 559; January 21, 1964) which was effective January 31, 1964. This amendment (39-6090, AD 64-02-06 R1) revises AD 64-02-06 and becomes effective December 27, 1988. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_64-02-06_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-02-06 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters Subject: Pylon and Tail Cone Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/27/1988 Make: Sikorsky Aircraft Corporation Model: S-58A | S-58B | S-58BT | S-58C | S-58D | S-58DT | S-58E | S-58ET | S-58F | S-58FT | S-58G | S-58H | ...Show more 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: 64-02-06 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6090 AD NUMBER: 64-02-06 R1 SUBJECT HEADING: Airworthiness Directives; All Sikorsky Model S-58 Series Helicopters ACTION: SUMMARY: DATES: Effective December 27, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-02-06 R1 SIKORSKY AIRCRAFT: Amendment 674 as amended by Amendment 39-6090. Applies to all Sikorsky Model S-58 series helicopters. Compliance is required as indicated unless already accomplished. Fatigue cracks have been found in the area of the rear three bolt holes of upper pylon folding hinge fitting P/N S1620-63130-2, the forward bolt holes of mating fitting P/N S1620-64127, the forward bolt hole of the lower pylon hinge fitting P/N S1620-64131, and the lug through which the hinge bolt passes of fittings P/N's S1620-64127 and S1620-64127-7. In order to preclude propagation of fatigue cracks in these areas and subsequent serious weakening of the pylon attachment, accomplish the following: (a) As of the effective date of this AD, conduct daily visual inspections of the area around the fitting bolt holes of all pylon and tail cone folding hinge fittings for cracks. Replace any cracked fittings before further flight. (b) Unless already accomplished, accomplish the following in accordance with Sikorsky Service Bulletin No. 58B20-11A within 100 hours' time in service after the effective date of this AD on all upper pylon hinge fittings P/N S1620-64127 with 1,900 hours' or more time in service, or prior to the accumulation of 2,000 hours' time in service on all fittings having less than 1,900 hours' time in service as of the effective date of this AD: (1) Remove all bushings from the hinges. (2) Rework and inspect the bore of each hole. (3) Install oversized replacement bushings P/N S1620-63129-7. (c) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, Aircraft Certification Service, ASW-110, FAA, Fort Worth, Texas 76193-0110. (d) In accordance with Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished. Airworthiness Directive 63-09-02 was superseded by AD 64-02-06 (Amendment 674; 29 FR 559; January 21, 1964) which was effective January 31, 1964. This amendment (39-6090, AD 64-02-06 R1) revises AD 64-02-06 and becomes effective December 27, 1988. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
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