AD 67-29-05

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AD Number:
67-29-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Sikorsky Model Type S61 Helicopters
Subject:
Rotary Wing Hub Hinge Pins
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/30/1967
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Superseded AD: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Superseded By: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: 67-29-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-501

AD NUMBER:   67-29-05

SUBJECT HEADING:   Airworthiness Directives; Sikorsky Model Type S61 Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective October 30, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-29-05 SIKORSKY AIRCRAFT: Amdt. 39-501 Part 39 Federal Register November 1, 1967. Applies to type S61 Helicopters.

Compliance required as indicated.

To prevent fatigue failures of the Rotary Wing Hub Horizontal Hinge Pins, P/N S6100-23020 and P/N S6110-23320, accomplish the following:

(a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, inspect the horizontal hinge pins in accordance with Sikorsky Service Bulletin No. 61B10-4 dated August 21, 1967 or later revisions approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region. Equivalent inspections may be approved by an FAA maintenance inspector.

(1) If a machining defect is found on the interior surface of the cylindrical part of the pin or on the inner surface of the part of the pin where the damper is attached (sections 1 or 3 of the pin as defined in the Sikorsky Service Bulletin) remove the hinge pin from service prior to further flight.

(2) If a machining defect is found on the interior surface of the tapered part of hinge pin (section 2 of the pins is defined in the Sikorsky Service Bulletin) inspect the external surface of this tapered section using a magnifying glass (2 power minimum). If a crack is found replace the hinge pin prior to further flight.

(3) If a defect is found on the interior surface of the tapered part of the hinge pin (section 2 of the pin is defined in the Sikorsky Service Bulletin) and no crack is detected on the external surface of this section:

(i) Perform a daily visual inspection of the external surface of section 2 using a magnifying glass (2 power minimum). If a crack is found remove the hinge pin from service before further flight.

(ii) The hinge pin must be removed from service within the next 50 hours' time in service.

This amendment effective October 30, 1967.

FOOTER: