EASA AD No : 20 11

- 0229

EASA Form 11 0 Page 1 / 2 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 11

- 0229

Date: 06 Dec ember 2011

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Age ncy [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemptio n].


### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :

A320 and A321 aeroplanes

TCDS Number : EASA.A.064

F oreign AD : Not applicable

Supersedure : None



### ATA 53 Fuselage

– Forward Fuselage Frame (FR) 24

– Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A 320

- 214, A 320

- 216, A 320

- 232, A 320

- 233, A 321

- 211, A 321

- 213 and A 321

- 231 aeroplanes, manufacturer serial number (MSN) 4338, 4371, 4374, 4375, 4377, 4381 to 4384 inclusive, 4386

, 4387, 4388, 4390 to 4402 inclusive, 4404 to 4409 inclusive, 4411 to 4417 inclusive, 4419 , 4420, 4421, 4423, 4424, 4426, 4429 to 4436 inclusive, 4438 to 4443 inclusive, 4445 to 4450 inclusive, 4453

, 4454, 4456 to 4469 inclusive, 4471, 4472, 4474 to 4481 inc lusive, 4483 to 4498 inclusive, 4500, 4504 , 4505, 4506 and 4509

.

Reason: During a quality check in production of an A3 20 family aeroplane , i t w as discovered that a fastener w as missing at FR 24 between stringer ( STRG ) 25 and STRG 26 on the right

- hand ( RH ) side

. The purpose of the missing fastener, a 4 mm diameter aluminium rivet

, Part Number (P/N) ASNA2050DXJ040

, is to connect the F R 24 to the F R 24 Tee. The hole where the fastener wa s missing was not drilled.
Further investigations rev ealed that the drilling was missing on the milling grid used for frame assembly of a limited group of aeroplanes

. This condition, if not corrected, could impair the structural integrity of the affected aeroplanes.
For the reasons described above, this AD requir es a special detailed inspection (SDI) of the affected area , and the accomplishment of the associated corrective actions.

Effective Date: 20 December 2011EASA AD No : 20 11

- 0229

EASA Form 11 0 Page 2 / 2 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Before the accumulation of 24 000 f light c ycles (FC) since the aeroplane first flight, accomplish a n SDI for cracks of the two adjacent fastener holes at FR 24 between ST R G 25 and ST R G 26 RH side in accordance with the instructions of Airbus S ervice Bulletin (S B ) A320

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- 1247

. (2 ) If , during the SDI as required by paragraph (1) of this AD, no crack is found, before the accumulation of 24 000 FC since the aeroplane first flight, accomplish the corrective actions (repair) in accordance with the instru ctions of Airbus SB A320

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- 1247

. ( 3 ) If , during the SDI as required by paragraph (1) of this AD, any crack is found, before next flight, contact Airbus for approved repair instructions and accomplish those instructions accordingly.

Ref. Public ations: Airb us Service Bulletin A320

- 53

- 1247 original issue

, dated 15 July 2011

. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.

2. This AD was posted on 03 November 2011 as PAD 11

- 113 for consultation until 01 December 2011

. No comments were received during the consultation period.

3. Enquiries regarding this A D should be referred to the Safety Information Section, Executive Directorate , EASA. E

- mail ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: AIRBUS

– Airworthiness Office

– EIAS

, Fax +33 5 61 93 44 51; E

- mail: account.airworth

- eas@airbus.com

.