EASA AD No : 20 1 2

- 0132

CAP .0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet

. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 12

- 0 132

Date : 19 Ju ly 201 2

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 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 operate 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, 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 and A319 aeroplanes

TCDS Number : EASA.A.064

F oreign AD : Not applicabl e

Supersedure : None



### ATA 53 Fuselage

– Forward Fuselage Frame (FR) 24 Circumferential J unction

– Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318

- 112, A319

- 111, A319

- 112, A319

- 115, A319

- 132 and A31 9

- 133 aeroplane models, manufacturer serial numbers (MSN) 3983, 3985, 3998, 4000, 4004, 4007, 4018, 4020, 4029, 4036, 4038, 4039, 4040, 4048, 4052, 4056, 4069, 4071, 4076, 4080, 4087, 4089, 4121, 4125, 4127, 4129, 4132, 4141, 4151, 4163, 4164, 4166, 4169, 4171, 4182, 4192, 4200, 4204, 4211, 4215, 4222, 4227, 4228, 4254, 4256, 4258, 4259, 4262, 4268, 4275, 4282, 4285, 4287, 4301, 4313, 4319, 4327, 4332 and 4336.

Reason: During a ground inspection of an A319 aeroplane in production , it w as discovered that on e fastener w as missing at stringer (STGR) 39 on the right

hand ( RH ) side of FR 24 (Section 13

- 14 side). The hole of the missing fastener was not drilled. The missing fastener, a 4.8 mm diameter titanium bolt

, Part Number (P/N) EN 6114 V3

- 7

, should connect t he cargo door keel beam foot to the circumferential butt

- strap and the section 13

- 14 lower shell panel. Further investigations have rev ealed that th e affected fastener has not been installed on a limited number of aeroplanes in production

, due to incorrect production instructions. This condition, if not corrected, could impair the structural integrity of the affected aeroplanes. For the reasons described above, this AD requires a special detailed inspection (SDI) of the affected area and , depending on findi ngs, the accomplishment of applicable corrective actions

.

Effective Date: 0 2 August 2012EASA AD No : 20 1 2

- 0132

CAP .0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 2 / 2 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: (1) Within the threshold indicated in Table 1 of this AD as applica ble to the aeroplane configuration

, accomplish a visual inspection of the fastener at FR 2 4 STGR 39 RH, in accordance with the instructions of Airbus Service Bulletin (SB) A320

- 53

- 1242

. Table 1

– Compliance time
Aeroplane Configuration Inspection Threshold

A319 aeroplanes except MSN 4151, 4228 and 4319

, and
A318 aeroplanes, pre

- mod 39195 , and on which Airbus SB A320

- 00

- 1219 has not been embodied in service. Before the accumulation of 5 000 flight cycles ( FC ) since first flight of the aeroplane , or within 4 300 FC after the effective date of this AD, whichever occurs later.

A318 aeroplanes, post

- mod 39195

, and on which Airbus SB A320

- 00

- 1219 has been embodied in service. Before the accumulation of 3 000 FC since first flight of the aeroplane

.

A319 aeroplanes, MSN 415 1

, 4228 and 4319 ( post

- mod 28238, 28162 and 28342 ) Before the accumulation of 2 500 FC since first flight of the aeroplane

.

(2) If, during the visual inspection as required by paragraph (1) of this AD, the fastener is found missing, within the compliance time indicated in Table 1 of this AD, as applicable, accomplish a SDI of the five holes surrounding the missing fastener at FR24 STGR 39 RH side to detect any crack, in accordance with the instructions of Airb us SB A320

- 53

- 1242. ( 3 ) If , during the SDI as requir ed by paragraph ( 2 ) of this AD, no crack is found, within the compliance time indicated in Table 1 of this AD, apply the corrective actions (repair) in accordance with the instructions of Airbus SB A320

- 53

- 1242. ( 4 ) If , during the SDI as required by paragr aph ( 2 ) of this AD, any crack is found, before next flight, contact Airbus for approved repair instructions and accomplish those instructions accordingly.

Ref. Public ations: Airbus SB A320

- 53

- 1242 original issue

, dated 22 May 201 2

. Airbus SB A320

- 00

- 1219 original issue dated 09 November 2010, Revision 01 dated 08 December 2010, Revision 02 dated 06 September 2011 or Revision 03 dated 28 March 2012. The use of later approved revisions of th e s e document s 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 05 June 2012 as PAD 1 2

- 0 59 f or consultation until 03 July 201 2 . The Comment Response Document can be fou nd at http://ad.easa.europa.eu

. 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 questi on concerning the technical c ontent 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

.