E ASA AD No.: 2013

- 0122

TE. CAP.0 011 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

. : 2013 - 0122

Date: 05 June 2013

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 Euro pean third countries that participate in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with E U 748/2012 , Part 21

. A.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 operate 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, Pa rt 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): A318 , A319 , A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not Appli cable
Supersedure: This AD supersedes DGAC France AD 92

- 201

- 030 dated 30 September 1992.



### ATA 53 Fuselage
– Belly Fairing and Keel Beam Side P anel Attachment

Angles
– Inspection / Replacement / Repair

Manufacturer(s): Airbus (Formerly Airbus Industr ie) Applicability: Airbus A318

- 111, A318

- 112, A318

- 121, A318

- 122, A319

- 111, A319

- 112, A319

- 113, A319

- 114, A319

- 115, A319

- 131, A319

- 132, A319

- 133, A320

- 111, A320

- 211, A320

- 212, A320

- 214, A320

- 215, A320

- 216, A320

- 231, A320

- 232, A320

- 233, A321

- 111, A321

- 112, A321

- 131, A321

- 211, A321

- 212, A321

- 213, A321

- 231 and A321

- 232 aeroplanes , all manufacturer serial numbers (MSN).
Reason: During the f atigue test campaign of the A320 family type design , cracks have been found at the lower riveting of the four t itanium an gle s which connect the belly fairing to the keel beam side panels between frame s FR4 0 and FR42 , on both sides of the fuselage

. This condition, i f not detected and corrected, could affect the structural integrity of the aeroplane

. In 1992, DGAC France issue d AD 92

- 201

- 030 to require reinforcement of the belly fairing structure, which addressed part of the unsafe condition. For the reason describe d above, this AD retains the requirements of DGAC France AD 92

- 201

- 030, which is superseded, and requires repetiti ve detail ed inspection s of the affected t itanium a ngle s and , depending on findings , repair or replacement of part s

. Effective Date: 19 June 2013E ASA AD No.: 2013

- 0122

TE. CAP.0 011 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. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: Re - statemen t of DGAC France AD 92 - 201 - 030 requirements : (1) For A320

- 111, A320

- 211 and A320

- 231 aeroplanes , MSN 0003 through 0092 inclu sive : Before exceeding 12 000 flight cycles ( FC ) since aeroplane first flight, reinforce the belly fairing structure in accordance with instructions of Airbus Service Bulletin (SB) A320

- 53

- 1014

. New requirements of this AD (for all aeroplanes) : ( 2 ) Within the compliance time defined in Table 1 of this AD, as applicable, and , thereafter , at intervals not to exceed 5 000 FC or 10 000 f l ight h ours (FH), whichever occur s first, accomplish a detail ed inspection of the four titanium angles between the belly fairing and the keel beam side panel in accordance with the instructions of Airbus SB A320

- 53

- 125 9

.

Table 1

- Initial inspection Compli ance time (whichever occurs later , A , B or C )
A Within 30 000 FC or 60 000 FH, w hichever occur s first after first flight of the aeroplane.

B Within 30 000 FC or 60 000 FH, whichever occurs first after modification of the aeroplane as required by paragrap h (1) of this AD , or after installation of new titanium angles , provided that , prior to installation, a rototest on the open holes has been accomplished with no findings , as specified in paragraph (3.2) of this AD.
C Within 3 000 FC or 6 000 FH, whichever occurs first after the effective date of this AD

.
(3) I f, during any inspection as required by paragraph ( 2 ) of this AD, no crack indication is detected , accomplish one of the following actions: (3.1) R epeat the inspection as required by paragraph (2) o f this AD ; or (3.2) B efore next flight after the inspection , remove all inspected titanium angles , accomplish a rototest on the open holes and, provided no cracks are found, install new titanium angles, in accordance with the instructions of Airbus SB A320

- 53

- 1259 . Thereafter, instead of paragraph (2), comply with the requirements of paragraph ( 5 ) of this AD. ( 4 ) If, during any inspection as required by paragraph (2) of this AD, crack indication is detected, before next flight, remove the affected titanium angle(s) and accomplish a rototest on the open holes and, provided no cracks are found, install new titanium angles, in accordance with the instructions of Airbus SB A320

- 53

- 125 9

. Thereafter, instead of paragraph (2), comply with the requirements of paragr aph ( 5 ) of this AD. (5) Within 30 000 FC or 60 000 FH, whichever occurs first a fter installation of new titanium angles as specified in paragraph (3 .2 ) of this AD, or as required by paragraph (4) of this AD, as applicable, and thereafter at intervals not t o exceed 5 000 FC or 1 0 000 FH, whichever occurs first, accomplish a detailed inspection of the four titanium angles between the belly fairing and the keel beam side panel in accordance with the instructions of Airbus SB A320

- 53

- 125 9

. (6) I f, during any in spection as required by paragraph ( 5 ) of this AD, crack indication is detected , before next flight, remove the affected titanium angles and accomplish a rototest on the open holes and, provided noE ASA AD No.: 2013

- 0122

TE. CAP.0 011 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. cracks are found, install new titanium angles, in accordanc e with the instructions of Airbus SB A320

- 53

- 125 9

. (7) If, during a ny rototest as required by paragraph (3), (4) or (6) of this AD, as applicable, a crack is found, before next flight, contact Airbus for approved repair instructions and accomplish those in structions accordingly

. ( 8 ) Repair or replacement of parts as required by this AD , as applicable, does not constitute terminating action for the repetitive inspections as required by this AD

. Ref. Public ations: Airbus SB A320

- 53

- 1014 original issue dated 25 June 1992, or Revision 01, dated 26 May 1993, or Revision 02, dated 01 September 1994. Airbus SB A320

- 53

- 1259 original i ssue, dated 06 November 2012

. The use of later approved revisions of th e s e document s is acceptable for compliance with the requiremen ts 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 13 February 2013 as PAD 13

- 034 for consultation until 13 March 2013. 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.euro pa.eu

. 4. For any question concerning the technical conte nt 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

.