Commonwealth legislation

AD/A320/214 - Rear Fuselage Structure Reinforcement

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Commonwealth

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legislative instrument

Plain English Summary

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This Airworthiness Directive requires operators of Airbus A321 aeroplanes that have not received Airbus modification 25791 or Service Bulletin A320‑53‑1130 to reinforce the rear fuselage between frames 62 and 64 to restore strength margin against undetected tail scrape (Applicability; Background). Work must be performed in accordance with DGAC AD F‑1999‑051‑125(B) or the stated service bulletin and completed by 5 July 2008; operators bear the cost and schedule the maintenance while CASA enforces the directive (Requirement; Compliance).

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Current sections

Direct links to the current provisions in AD/A320/214 - Rear Fuselage Structure Reinforcement.

Airbus Industrie A319, A320 and A321 Ser

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/214	Rear Fuselage Structure Reinforcement	6/2008

Applicability:	All Model A321 aircraft, without AIRBUS modification 25791 incorporated in production or AIRBUS Service Bulletin A320-53-1130 incorporated in service.
Requirement:	Action in accordance with DGAC AD F-1999-051-125(B).Note: AIRBUS Service Bulletin A320-53-1130 original issue, or later DGAC/EASA approved revision, refers.
Compliance:	Unless already accomplished, before 5 July 2008.
	This Airworthiness Directive becomes effective on 5 June 2008.
Background:	The rear fuselage structure requires reinforcement between frames 62 and 64, in order to increase the strength margin in the case of undetected tail scrape of the rear of the fuselage with the ground.

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David Villiers
Delegate of the Civil Aviation Safety Authority

16 April 2008

AD/A320/214

Rear Fuselage Structure Reinforcement

6/2008

Source text

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

Airbus Industrie A319, A320 and A321 Ser Airbus Industrie A319, A320 and A321 Series Aeroplanes

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/214	Rear Fuselage Structure Reinforcement	6/2008

Applicability:	All Model A321 aircraft, without AIRBUS modification 25791 incorporated in production or AIRBUS Service Bulletin A320-53-1130 incorporated in service.
Requirement:	Action in accordance with DGAC AD F-1999-051-125(B).Note: AIRBUS Service Bulletin A320-53-1130 original issue, or later DGAC/EASA approved revision, refers.
Compliance:	Unless already accomplished, before 5 July 2008.
	This Airworthiness Directive becomes effective on 5 June 2008.
Background:	The rear fuselage structure requires reinforcement between frames 62 and 64, in order to increase the strength margin in the case of undetected tail scrape of the rear of the fuselage with the ground.

AD/A320/214 - Rear Fuselage Structure Reinforcement

Plain English Summary

Deep dive

Current sections

Airbus Industrie A319, A320 and A321 Series Aeroplanes

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/214

AD/A320/214

Rear Fuselage Structure Reinforcement

Rear Fuselage Structure Reinforcement

6/2008

6/2008

Source text

Airbus Industrie A319, A320 and A321 Ser Airbus Industrie A319, A320 and A321 Series Aeroplanes

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/214 AD/A320/214

AD/A320/214

Rear Fuselage Structure Reinforcement Rear Fuselage Structure Reinforcement

Rear Fuselage Structure Reinforcement

6/2008 6/2008

6/2008