Document ID: chunk:federal_register_of_legislation:F2005L00615:body:0
Version: federal_register_of_legislation:F2005L00615
Segment Type: other
Provision Reference: 
Character Range: 0–2156

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/S-62/6 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Sikorsky S-62 Series Helicopters
AD/S-62/6 Amdt 1  Main Gearbox Primary Servo  4/2005
                  Mechanism Supports

Applicability:  Model S-62A helicopters equipped with part number S14-40-2415 primary servo mechanism support fittings.
Requirement:       1. Inspect in accordance with Part I subparagraph A and B of Accomplishment Instructions of Sikorsky Aircraft Service Bulletin (SB) 62B40-8, dated 1 October 1971.

                   2. Inspect in accordance with Part I subparagraph B of Accomplishment Instructions of SB 62B40-8.

                   3. Conduct a fluorescent magnetic particle inspection in accordance with Part II of Accomplishment Instructions of SB 62B40-8.

                Note:  FAA AD 71-26-3 Amdt 39-1363 refers.
Compliance:        1. Unless the initial inspection is already accomplished; within 120 flight hours after 14 April 2005.

                   2. Inspect thereafter at intervals not to exceed 120 flight hours.

                   3. At gearbox overhaul or 1,250 total flight hours, whichever occurs first.
                This Amendment becomes effective on 14 April 2005.
Background:     The related FAA AD was prompted by a report of a fracture radiating from a bolt hole in one of the four support fitting attachment lugs.  A support fitting retaining bolt was also fractured.

David Villiers
Delegate of the Civil Aviation Safety Authority

2 March 2005