AD/Bell 430/1 Amdt 2 Tail Rotor Blade (Cth)

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/BELL 430/1 Amdt 1 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.

Bell Helicopter Textron Canada (BHTC) 430 Series Helicopters

AD/BELL 430/1 Amdt 2 Tail Rotor Blade 3/2005

Applicability:

Model 430 helicopters, serial numbers 49001 through 49107, equipped with tail rotor blades, part numbers 222-016-001-123 and 222-016-001-131.

Requirement:

1.    Inspect the tail rotor blades in accordance with Part I of Bell Helicopter Textron Canada Alert Service Bulletin (ASB) 430-04-31 original issue, Revision A, or later Transport Canada approved revision.

2.    Inspect the tail rotor blades in accordance with Part II of ASB 430-04-31 original issue, Revision A, or later Transport Canada approved revision.

Note:  Transport Canada AD CF-2004-21 R1 refers.

Compliance:

1.    Within 3 flight hours after 3 December 2004, and thereafter at intervals not to exceed 3 flight hours.

2.    Within 50 flight hours after 3 December 2004, and thereafter at intervals not to exceed 50 flight hours.

This Directive shall be entered on the Maintenance Release as maintenance required.  The Requirement 1 inspection may be performed and certified by the Pilot in Command who has been trained to do the inspection by an appropriately qualified person.  In this case, a copy of the Requirement document and this Directive is to be carried on the aircraft.

The compliance times remain unchanged by this issue.

This Amendment becomes effective on 17 March 2005.

Background:

Reports were received of three occurrences of cracked tail rotor blades; discovered during scheduled inspection.  Two cracks initiated from the outboard bearing bore underneath the flanged sleeves.  The third crack initiated from the inboard bearing bore.  Corrosion and machining burrs are suspected as the crack initiators.

Amendment 1 clarified applicability and allowed the pilot to accomplish Requirement 1 inspections.

Amendment 2 is issued in response to a revision of the related Transport Canada AD, which expands applicability but with no change to technical content.

David Punshon
Delegate of the Civil Aviation Safety Authority

4 February 2005