EASA AD No : 2012-0132

CAP.00110-001 © 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.: 2012-0132

Date: 19 July 2012

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 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, 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) :

A318 and A319 aeroplanes

TCDS Number : EASA.A.064

Foreign AD : Not applicable

Supersedure : None

ATA 53 Fuselage – Forward Fuselage Frame (FR) 24 Circumferential 

Junction – Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-112, A319-111, A319-112, A319-115, A319-132 and A319-133 

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 was 

discovered that one fastener was missing at stringer (STGR) 39 on the righthand (RH) side of FR24 (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 the cargo door keel beam foot to 

the circumferential butt-strap and the section 13-14 lower shell panel. Further 

investigations have revealed that the 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 findings, the 

accomplishment of applicable corrective actions.

Effective Date: 02 August 2012
EASA AD No : 2012-0132

CAP.00110-001 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the threshold indicated in Table 1 of this AD as applicable to the 

aeroplane configuration, accomplish a visual inspection of the fastener at 

FR24 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 4151, 

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 Airbus SB A320-53-1242.

(3) If, during the SDI as required 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 paragraph (2) of this AD, any crack is 

found, before next flight, contact Airbus for approved repair instructions 

and accomplish those instructions accordingly.

Ref. Publications: Airbus SB A320-53-1242 original issue, dated 22 May 2012.

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 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 05 June 2012 as PAD 12-059 for consultation until 

03 July 2012. 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.