COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Bell Helicopter Textron 204 Series Helicopters
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BELL 204/44 and issues the following AD under subregulation 39.1 (1) of CAR 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.
AD/BELL 204/44
Amdt 1
Main Rotor Mast 10/2000 TX
Applicability: Model 204B helicopters with main rotor mast, part number 204-011-450-001, -007, - 105, -113, or -119, or main rotor trunnion part number 204-011-105-001, or -103, installed.
Requirement: Action in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52.
Note: A copy of FAA AD 2000-15-52 may be obtained from the FAA Internet site http://av-info.faa.gov/ad or from the Authority.
Compliance: Before further flight after 9 August 2000 for paragraph (a) of the Requirement document, unless already accomplished. As specified in the Requirement document for compliance times of other required actions.
This Amendment becomes effective on 9 August 2000.
Background: FAA AD 98-24-15 was issued to prevent failure of the main rotor mast due to fatigue. That directive required that a component history card or approved equivalent, record torque events as a Retirement Index Number (RIN) for these components. AD 2000- 08-52 inspects for damage to the mast, increases accumulated RIN accordingly, and also reduces the overall RIN.
Amendment 1 is issued in response to a new FAA AD which was prompted by a report of another cracked main rotor mast. Metallurgical inspection revealed that the mast cracked as a result of fatigue in snap ring groove radii that were smaller than the
0.020 inch minimum allowable dimension. The FAA has concluded that several corrections to the RIN counting procedure are required based on a review of the fatigue data and previously issued Directives.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
The original issue of this Airworthiness Directive was to became effective on 10 August 2000.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 8 August 2000
The above AD is notified in the Commonwealth of Australia Gazette on 9 August 2000.