AD 71-26-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Sikorsky Aircraft Corporation | S-55 | Airworthiness Directives; Sikorsky Models S-62A and S-55 Helicopters |
| aircraft | Sikorsky Aircraft Corporation | S62A | Airworthiness Directives; Sikorsky Models S-62A and S-55 Helicopters |
Unsafe Condition
Failure of the S-62A and S-55 Servo Support Bracket P/N 1440-2415.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the servo support bracket within 25 hours in service after the AD's effective date if not done in last 95 hours. Subsequent inspections every 120 hours in service. Conduct fluorescent magnetic particle inspection at gear box overhaul or 1250 hours, whichever comes first.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 25 hours in service after December 30, 1971, and every 120 hours thereafter. Fluorescent magnetic particle inspection required at gear box overhaul or 1250 hours in service, whichever comes first.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Sikorsky Models S-62A and S-55 Helicopters certified in all categories.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Servo Support Bracket
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_71-26-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 71-26-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Sikorsky Models S-62A and S-55 Helicopters Subject: Servo Support Bracket Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/30/1971 Make: Sikorsky Aircraft Corporation Model: S-55 | S62A Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185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: 71-26-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1363 AD NUMBER: 71-26-03 SUBJECT HEADING: Airworthiness Directives; Sikorsky Models S-62A and S-55 Helicopters ACTION: SUMMARY: DATES: Effective December 30, 1971. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 71-26-03 SIKORSKY AIRCRAFT: Amdt. 39-1363. Applies to Sikorsky S-62A and S- 55 type Helicopters certified in all categories. Compliance required as follows: To preclude the failure of the S-62A and S-55 Servo Support Bracket P/N 1440-2415. 1. Unless already accomplished within the last 95 hours in service, inspect the servo support bracket within the next 25 hours in service after the effective date of this AD, in accordance with Part I subparagraph A and B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later FAA- approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Inspect the bracket within 120 hours in service after the inspection in paragraph 1 of this airworthiness directive and every 120 hours thereafter in accordance with Part I subparagraph B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 3. Conduct fluorescent magnetic particle inspection in accordance with Part II Accomplishment Instructions of SIK S/B 55B40-6 or 62B40-8 as applicable at gear box overhaul or 1250 hours, whichever comes first; or an alternate method approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective December 30, 1971. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_71-26-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 71-26-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Sikorsky Models S-62A and S-55 Helicopters Subject: Servo Support Bracket Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 12/30/1971 Make: Sikorsky Aircraft Corporation Model: S-55 | S62A 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: 71-26-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1363 AD NUMBER: 71-26-03 SUBJECT HEADING: Airworthiness Directives; Sikorsky Models S-62A and S-55 Helicopters ACTION: SUMMARY: DATES: Effective December 30, 1971. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 71-26-03 SIKORSKY AIRCRAFT: Amdt. 39-1363. Applies to Sikorsky S-62A and S- 55 type Helicopters certified in all categories. Compliance required as follows: To preclude the failure of the S-62A and S-55 Servo Support Bracket P/N 1440-2415. 1. Unless already accomplished within the last 95 hours in service, inspect the servo support bracket within the next 25 hours in service after the effective date of this AD, in accordance with Part I subparagraph A and B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later FAA- approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Inspect the bracket within 120 hours in service after the inspection in paragraph 1 of this airworthiness directive and every 120 hours thereafter in accordance with Part I subparagraph B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 3. Conduct fluorescent magnetic particle inspection in accordance with Part II Accomplishment Instructions of SIK S/B 55B40-6 or 62B40-8 as applicable at gear box overhaul or 1250 hours, whichever comes first; or an alternate method approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective December 30, 1971. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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