AD 79-12-10

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AD Number:
79-12-10
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SIKORSKY S-61 series helicopters
Subject:
Tail Rotor Blades
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
Sikorsky Aircraft Corporation
Model:
S-61A | S-61D | S-61E | S-61L | S-61N | S-61NM | S-61R | S-61V
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Superseded AD: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Superseded By: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: 79-12-10
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3496

AD NUMBER:   79-12-10

SUBJECT HEADING:   Airworthiness Directives; SIKORSKY S-61 series helicopters

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
79-12-10 SIKORSKY: Amendment 39-3496. Applies to S-61 series helicopters certificated in all categories, including FAA certificated military counterparts, equipped with P/Ns S6115-30001 or S6117-30001 series tail rotor blades.

To preclude the possibility of failure of the tail rotor blade, accomplish the following:

1. Inspect tail rotor blades, P/Ns S6115-30001 and S6117-30001, series for cracks in accordance with the following:

a. Prior to further flight, unless already accomplished, dye penetrant inspect the inboard 32 inch section in accordance with Sikorsky Aircraft Service Bulletin 61B15-26.

b. Thereafter, prior to the first flight of the day, conduct visual inspections of the blades in accordance with Sikorsky Service Bulletin 61B15-1E.

c. Within the next six hours time in service, unless already accomplished, ultrasonically inspect the blades for spar and skin cracks in accordance with Sikorsky Service Bulletin 61B15-26. Thereafter for blades with over 1200 hours time in service, inspect ultrasonically at intervals not to exceed six hours time in service in accordance with Sikorsky Service Bulletin 61B15-26.

2. Prior to further flight, unless already accomplished, perform a one-time dye penetrant or Zyglo inspection of the tail rotor gearbox mounting feet for cracks in accordance with Sikorsky Service Bulletin 61B15-26.

3. If a crack is found during the inspection of paragraph 1 or 2 above, replace the cracked blade or gearbox with a new or serviceable component, prior to further flight. A serviceable blade or gearbox is one that has been inspected in accordance with the subject service bulletins and found to be free of cracks.

4. Report in writing any cracks found during the inspections of paragraph 1 or 2 above to: Chief, Engineering and Manufacturing Branch, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Each report must include the length and location of the cracks and total time in service of the blade or gearbox. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at the FAA, New England Headquarters, Burlington, Massachusetts.

This amendment becomes effective upon publication in the Federal Register.

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