Commonwealth legislation

AD/A320/94 Amdt 1 - Reinforcement of Frame 35 between Stringers 30 and 31

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Commonwealth

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legislative instrument

Plain English Summary

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This AD requires Airbus A319/A320/A321 (A320‑111, ‑211, ‑231) operators to inspect fastener holes at Frame 35 between stringers 30 and 31 and replace affected fasteners, following Airbus Service Bulletin A320‑53‑1137 Revision 2, unless Airbus modification 20903 or that SB has already been applied. Compliance is set by flight‑cycle thresholds (by 18,400 cycles or within 3,500 cycles after 21 March 2002, but not beyond 20,000). Aircraft operators fund inspections and replacements; CASA enforces the requirement under CAR 1998 subreg 39.1(1).

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Current sections

Direct links to the current provisions in AD/A320/94 Amdt 1 - Reinforcement of Frame 35 between Stringers 30 and 31.

AD/A320/94 Amdt 1 - Reinforcement of Frame 35 between Stringers 30 and 31

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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AIRWORTHINESS DIRECTIVE

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For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/A320/94 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.

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/94

Amdt 1

Reinforcement of Frame 35 between Stringers 30 and 31

3/2002

Applicability: All Model A320-111, -211, and -231 aircraft, except aircraft which have received Airbus Industrie modification 20903 in-production or Service Bulletin A320-53-1137 in-service.

Requirement: Replace the affected fasteners after inspection of the fastener holes, in accordance with Airbus Industrie Service Bulletin A320-53-1137, Revision 2.

Note: DGAC AD 2002-032(B) refers.

Compliance: Before the accumulation of 18,400 flight cycles or within 3,500 flight cycles after 21 March 2002, whichever occurs later, without exceeding 20,000 total flight cycles; unless already accomplished.

This amendment becomes effective on 21 March 2002.

Background: During full-scale fatigue test, cracks were found at rivet holes located at FR35, between STGR30 and STRG31, left and right hand sides. This Directive provides reinforcement of the affected area.

Amendment 1 is issued in response to a new DGAC AD which revises the threshold for accomplishment of the required modification. This action results from a survey of the A320 fleet, which highlighted some differences between the mission parameters of in-service aircraft and those originally considered.

The original issue of this Airworthiness Directive became effective on 16 July 1998.

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David Alan Villiers

Delegate of the Civil Aviation Safety Authority 8 February 2002

View image in the official source

The above AD is notified in the Commonwealth of Australia Gazette on 27 February 2002.

Page 1 of 1

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/A320/94 Amdt 1 - Reinforcement of Frame 35 between Stringers 30 and 31

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/A320/94 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.

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/94

Amdt 1

Reinforcement of Frame 35 between Stringers 30 and 31

3/2002

Applicability: All Model A320-111, -211, and -231 aircraft, except aircraft which have received Airbus Industrie modification 20903 in-production or Service Bulletin A320-53-1137 in-service.

Requirement: Replace the affected fasteners after inspection of the fastener holes, in accordance with Airbus Industrie Service Bulletin A320-53-1137, Revision 2.

Note: DGAC AD 2002-032(B) refers.

This amendment becomes effective on 21 March 2002.

The original issue of this Airworthiness Directive became effective on 16 July 1998.

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 8 February 2002