EASA AD No.: 20 1 4

- 0065

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 4 - 0065

Date: 14 M arch 2014

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 EU 748/2012, Part 21.A.3B. In accordan ce 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 Agency [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) exemption]

. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A320 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable
Supersedure: This AD supersedes DGAC France AD 2002

- 342 dated 26 June 2002

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### ATA 57 Wings

– Centre Wing Box Lower Surface Panel

– Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie) Applicability: Airbus A320

- 211, A320

- 212 and A320

- 231 aeroplanes, all m anufacturer s erial n umbers (MSN), except those on which Airbus Modification (mod) 22418 has been embodied in production.
Reason: During center fuselage certification full scale test, damage was found in the center wing box (CWB) lower surface panel. This condition, if not detected and corrected, could affect the structural integrity of the CWB. To prevent such damage , Airbus develop ed mod 22418 which consist s in shot

peening of the lower panel in the related area. Mod 22418 has been embodied in production from aeroplane MSN 0359

. For unmodified in

- service aeroplane s, Airbus issued Service Bulletin (SB) A320

- 57

- 1082 to introduce repetitive High Frequency Eddy Current (H FEC) inspection s on the external face of the center wing box lower panel between Frame (FR)41 and FR42 to detect damage

. DGAC France issued AD 2002

- 342 to require these inspections and, depending on findings, applicable corrective action(s). Airbus also is sued SB A320

- 57

- 1043 as an optional terminating action for the repetitive inspection s required by DGAC France AD 2002

- 342. Since th at AD was issued , the results of a survey, carried out on the A320 fleet, highlighted some differences between the mission parameters , mainly on the weight of fuel at landing and on the average flight duration, which are higher than those defined for the analysis of the fatigue related tasks.EASA AD No.: 20 1 4

- 0065

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. These findings have led to an adjustment of the A320 reference fatigue mission. Conse quently, the threshold and intervals of the se repetitive inspection s have been revised and a new threshold figure expressed in flight hours (FH) has been established

. In addition, it has been identified that , on aeroplanes that have been modified in accordance with Airbus SB A320

- 57

- 1043 ( Airbus m od 22418) at R evision 0 5 or an earlier Revision , the shot peening may have been im properly done on the Chromic Acid Anodizing ( CAA ) protection, whic h has no fatigue benefit effect. Therefore, the inspection s per Airbus SB A320

- 57

- 1082 are required again on these aeroplanes

. Consequently , new shot

- peening procedures with proper CAA protection removal instructions ha ve been developed and their embodiment through Airbus SB A320

- 57

- 1043 Revision 06 cancels the repetitive inspection s per Airbus SB A320

- 57

- 1082 , as required by DGAC France AD 2002

- 342

. For the reason s describe d above, this new AD retains the requirements of DGAC France AD 2 002

- 342 , which is superseded , but requires these actions to be accomplis hed within reduced thresholds and interval s

. In addition, the optional terminating action provision ( SB A320

- 57

- 1043 ) is amended by including reference to the SB at Revision 06.

Effective Date: 28 March 2014 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) For aeroplanes i n pre - SB A320
- 57 - 1043 ( at any revision ) configuration on which a repair ha s been accomplished in accordance with Airbus SB A320
- 57 - 1082 ( at any revision up to Revision 03 inclusive ) : Within 30 days after the effective date of this AD, contact Airbus for approved repair instructions and accomplish those instructions accordingly. ( 2 ) For all aeroplanes : Within the compliance time s as defined in Table 1 or Table 2 of this AD, as applicable, and , thereafter , a t interval s not to exceed 7 200 flight cycles ( FC ) or 14 400 FH, whichever occurs first , accomplish a HFEC inspection of the CWB lower surface panel in accordance with the instructions of Airbus SB A320

- 57

- 1082 Revision 04.
Table 1

– Initial Inspection for aeroplanes in p re - SB A320

- 57

- 1043

(any revision) configuration Compliance Time (w hichever occurs later, A or B )
A Within 20 7 00 FC or 41 400 FH, whichever occurs first since aeroplane first flight
B Within 7 200 FC or 14 400 FH , whichever occurs first since last inspection per Airbus SB A320

- 57

- 1082 up to R evision 03

Table 2

– Initial Inspection for aeroplanes in p ost

- SB A320

- 57

- 1043

(any revision up to Revision 05) configuration Compliance Time (whichever occurs later, A , B or C )
A Within 7 200 FC or 14 400 FH, whichever occurs first since embodiment of Airbus SB A320

- 57

- 1043
B Within 3 750 FC or 7 500 FH, whichever occurs first after 31 July 2012 (as specified in SB A320

- 57

- 1082 at Revision 04)
C Within 850 FC or 1 700 FH, whichever occurs first after the effective date of this ADEASA AD No.: 20 1 4

- 0065

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. (3) If , during any inspection a s required by paragraph (2) of this AD, any damage is found, before next flight, contact Airbus for approved repair instructions and , within the compliance time specified in th o s e instruction s , accomplish the repair , including any follow

- on actions, as applicable, accordingly

. ( 4 ) Modification of an aeroplane in accordance with the instructions of Airbus SB A320

- 57

- 1043 R evision 06 constitutes term inating action for the repetitive inspections as required by paragraph (2) of this AD for that aeroplane

. Ref. Public ations: Airbus SB A320

- 57

- 1043 o riginal issue dated 16 February 1993, Revision 01 dated 14 June 1996, R evision 02 dated 14 May 1997, Revision 03 dated 24 October 1997, Revision 04 dated 15 March 1999, Revision 05 dated 30 April 2002, or Revision 06 dated 05 December 2013

. Airbus SB A320

- 57

- 1082 o riginal issue dated 31 October 1996, Revision 01 dated 10 December 1997, R evision 02 dated 26 July 1999, Revisio n 03 dated 30 April 2002, or Revision 04 dated 05 December 2013

. The u se of later approved revisions of these documents 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 24 January 2014 as PAD 14

- 02 0 for consultation until 2 1 February 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD 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

.