AD 80-14-16 R1

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AD Number:
80-14-16 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SIKORSKY AIRCRAFT Model S-76A Series Helicopters
Subject:
Main Rotor Blade Spindle
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/09/1980
Make:
Sikorsky Aircraft Corporation
Model:
S-76A
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Superseded AD: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Superseded By: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: 80-14-16 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3941

AD NUMBER:   80-14-16 R1

SUBJECT HEADING:   Airworthiness Directives; SIKORSKY AIRCRAFT Model S-76A Series Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective October 9, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-14-16 R1 SIKORSKY AIRCRAFT: Amendment 39-3837 as amended by Amendment 39-3941. Applies to S-76A series helicopters certificated in all categories.

To prevent operation with a displaced shear bearing inner race and a possible cracked main rotor blade spindle accomplish the following:

1. Compliance required as indicated, unless already accomplished under the requirements of telegraphic airworthiness directive (TAD) T80NE-21, or accomplished prior to issuance of the original FAA airworthiness certificate.

a. Prior to further flight, inspect the P/N 76102-08000-041 main rotor blade spindle assemblies in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraph G(1) through G(3), dated April 24, 1980.

b. Prior to further flight, remove from service any P/N 76102-08001 main rotor blade spindles found to have a missing or displaced (beyond 1/2 inch) P/N SB 5206-102/-103 spindle shear bearing inner race. Spindle assemblies, where the spindle sear bearing has been previously found, prior to April 24, 1980, missing, displaced (any dimension), or reworked in any manner, must also be replaced prior to further flight in accordance with the applicable procedures described in this AD.

c. Within the next 25 hours time in service, after July 12, 1980, modify and repetitively inspect the P/N 76102-08000 main rotor blade spindle assemblies in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraphs G(4) and G(5), dated April 24, 1980.

Note: The requirements of this paragraph are an interim action which must be utilized until the components for the required modification described in paragraph 1d herein become available.

d. Prior to February 15, 1981, remove from service all "Cable-TYs" installed on main rotor blade spindle assemblies in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraph G(4), and replace with sleeve type retainers 76102-08055-101 and sleeve straps 76102-08055-103 in accordance with Paragraph 2C of Sikorsky Service Bulletin 76-65-15, dated September 17, 1980.

Accomplishment of the modification in accordance with paragraph 1d contained herein constitutes terminating action for this AD. Refer to Chapters 4 and 5 of the Sikorsky S-76 Maintenance Manual, SA 4047-76-2, for mandatory inspections.

2. Applies to main rotor blade spindles, P/N 76102-08001-041, with 200 or more hours time in service, compliance required within the next 5 hours time in service after July 12, 1980, unless already accomplished under the requirements of TAD T80NE-21.

a. Remove and inspect the main rotor blade spindles for cracks in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraph G(6), dated April 24, 1980.

b. If a crack indication is found, replace the main rotor blade spindle with a new or serviceable main rotor blade spindle, prior to next flight, in accordance with Sikorsky S-76 Maintenance Manual, SA 4047-76-2, Section 65-12-02.

c. If no crack indication is found, reinstall the main rotor blade spindle in accordance with the procedures in Paragraph 2.b of this AD.

3. Report within 24 hours any discrepancies found and the main rotor blade spindle times in service, to the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803.

Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.

4. Aircraft may be ferried to a base for maintenance, except for aircraft found to have a missing spindle shear bearing inner race, in accordance with Section 21.197 of the Federal Aviation Regulations.

NOTE: Sikorsky references noted herein pertain to this AD:

a. Sikorsky Alert Service Bulletin 76-65-13A, dated April 24, 1980.
b. Sikorsky S-76 Maintenance Manual, SA 4047-76-2, Section 65-12-O2.
c. Sikorsky Service Bulletin 76-65-15, dated September 17, 1980.

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, Division of United Technologies Corporation, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, 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 Region Headquarters, Burlington, Massachusetts.

Amendment 39-3837 became effective July 12, 1980, as to all persons except those persons to whom it was made immediately effective by the telegram dated April 24, 1980.

This amendment 39-3941 becomes effective October 9, 1980.

FOOTER: