COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Bell Helicopter Textron 205 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 205/1 Amdt 31 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 205/1
Amdt 32
Airworthiness Limitations 10/2000 TX
Applicability: For Requirement 1: All Model 205A, 205A-1 and 205B helicopters.
For Requirement 2: Model 205A, 205A-1, and 205B 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: 1. Retire components from service at the times specified in the Mandatory Airworthiness Limitations Schedule, Section 4, of the Bell 205A-1 Maintenance Manual (Revision 3 or later), with the following exceptions and additions:
Part Description Retirement Life
Drive link to rotating swashplate bolts 500 hours
2. For the main rotor mast and trunnion, determine the accumulated Retirement Index Number (RIN), inspect and 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: For Requirement 1: At the times specified in the Requirement document.
For Requirement 2: 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.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: This Airworthiness Directive mandates life limits and inspections for critical components, to prevent their failure in service from metal fatigue.
Amendment 32 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.
Amendment 31 added Requirement 2, developed by Bell and the FAA to better control fatigue in the main rotor mast and trunnion following a fatigue-related accident. The latest revision of the Mandatory Airworthiness Limitations Schedule was added to Requirement 1. This latest revision reduces the life of P/N 204-011- 728-(all dash number) tail rotor grips to 300 hours, so there is no longer a need for a special listing. Requirement 1 was also reformatted slightly, without technical change.
Amendment 31 of this Airworthiness Directive became effective on 28 April 2000.
Amendment 30, which updated the revision of the Maintenance Manual, became effective on 8 August 1991.
The original issue of this Airworthiness Directive became effective on 5 September 1968.
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.