COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (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/A320/114 Frame 36 - Longitudinal Beams of the Pressure Panel

Applicability: All Model A320 aircraft, MSN 0002 to MSN 0107 without Airbus Industrie

3/2001

modification 21202/K1432 in production or Airbus Industrie Service Bulletin A320- 53-1029 in service.

Requirement: 1. Inspect the longitudinal beams in accordance with the Airbus Industrie Service Bulletin A320-53-1030.

2.    If no crack is evident, repeat the Requirement 1 inspection.

3.    If cracks are evident, apply corrective actions and the corresponding inspection program.

Note: DGAC AD 2000-531-155(B) refers.

Compliance: 1. Before accumulation of 30,000 flights since entry into service.

2.    At intervals not exceeding 6,000 flights for aircraft without a centre tank and 18,000 flights for aircraft with a centre tank. Alternatively, embody Airbus Industrie Service Bulletin A320-53-1029, which is terminating action for the repeat inspection.

3.    At threshold and intervals defined in accordance with the instructions given in Airbus Industrie Service Bulletin A320-53-1030.

This Airworthiness Directive becomes effective on 22 March 2001.

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Background:  During fatigue tests, cracks were found around the fasteners connecting the pressure panel with the flexible bracket at FR36 adjacent to the longitudinal beams, left hand and right hand.

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 2 February 2001

The above AD is notified in the Commonwealth of Australia Gazette on 21 February 2001.