EASA AD No.: 2014-0053

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0053

Date: 07 March 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 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):

A320 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD 95-098-066 dated 24 May 1995.

ATA 57 Wing – Center Wing / Lower Ribs at Frame 36 Junction –

Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A320-211 and A320-231 aeroplanes, all manufacturer serial numbers 

(MSN) up to MSN 0084 inclusive.

Reason: During full scale fatigue tests on the Airbus A320 test specimen, cracks were

found in the rib flange on the front spar side perpendicular to vertical posts at 

frame (FR) 36. It was determined that similar cracks could develop on certain 

in-service aeroplanes.

This condition, if not detected and corrected, could affect the wing structural 

integrity.

To reduce the risk of crack initiation, two modifications for aeroplanes in 

production and one modification for in-service aeroplanes were developed by 

Airbus: Prior to MSN 0085, the adaptation modification (Mod) 20976 was 

applied in production, consisting in installing shims under the fasteners linking 

the rib flange, the lower corner, the front spar and its vertical stiffener; from 

MSN 0085 onwards, the serial Mod 20908 was applied in production, 

consisting in installing reinforced lower surface rib flanges at front spar level. 

Airbus issued Service Bulletin (SB) A320-57-1013 for affected in-service 

aeroplanes, and DGAC France issued AD 95-098-066 to require installation of 

shims under the fasteners linking the rib flange, the lower corner, the front spar 

and its vertical stiffener.

Following a recent analysis, Airbus identified the need for repetitive inspections

for aeroplanes on which Airbus SB A320-57-1013 or production Mod 20976 

has been embodied.

For the reason described above, this AD retains the requirements of DGAC 
EASA AD No.: 2014-0053

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France AD 95-098-066, which is superseded, and requires repetitive 

inspections of the center wing lower ribs at FR 36 and, depending on findings, 

accomplishment of a repair. 

After EASA issued PAD 14-013, it was discovered that additional work, to be 

included in Revision 01 of Airbus SB A320-57-1175, is required to accomplish 

the inspections. This Final AD has been amended accordingly.

Effective Date: 21 March 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Restatement of requirements of DGAC France AD 95-098-066:

(1) For aeroplanes with MSN 005 to 008 inclusive, MSN 010 to 014 inclusive, 

and MSN 016 to 042 inclusive, before accumulating 16 000 flight cycles 

(FC) since aeroplane first flight, reinforce the pressure floor fittings in 

accordance with the instructions of Airbus SB A320-57-1013.

New requirements of this AD:

(2) For all aeroplanes to which this AD applies: Within the compliance time 

defined in Table 1 of this AD, as applicable to aeroplane configuration, 

and, thereafter, at intervals not to exceed 32 500 FC or 65 000 flight hours 

(FH), whichever occurs first, accomplish a special detail inspection (SDI) of 

the radius of the rib flanges and a rototest inspection of the holes in the rib 

flanges on front spar side in accordance with the instructions of Airbus SB

A320-57-1175.

In addition to the accomplishment instructions of Airbus SB A320-57-1175, 

during each inspection, remove the shims and fasteners on the rib flange 

on the front spar side (installed as per Mod 20976, or through Airbus SB 

A320-57-1013), accomplish a SDI of the radius of the rib flanges, and 

accomplish a rototest inspection, before reinstalling the shims and 

fasteners on the rib flange.

The detailed accomplishment instructions for this additional work will be 

published in Airbus SB A320-57-1175 Revision 01. Until the revised SB is 

available (expected end of March 2014), operators should contact Airbus 

to request all necessary instructions for this additional work.

Table 1 Inspection Threshold

Aeroplane 

Configuration

Compliance Time

(whichever occurs later, A or B)

Mod 20976 has been 

embodied

A

Before exceeding 47 800 FC or

95 600 FH, whichever occurs first

since aeroplane first flight

B

Within 850 FC or 1 700 FH,

whichever occurs first after the 

effective date of this AD

Airbus SB A320-57-1013 

(at any revision) has been 

embodied

A

Before exceeding 10 700 FC or

21 500 FH, whichever occurs first 

after Airbus SB A320-57-1013 

embodiment

B

Within 850 FC or 1 700 FH,

whichever occurs first after the 

effective date of this AD

(3) For aeroplanes on which an initial inspection, in accordance with the 

instructions of Airbus SB A320-57-1175 at original issue, has already been 

accomplished, without having accomplished additional work as specified in 
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paragraph (2) of this AD, within the compliance time as defined in Table 1 

of this AD, as applicable, accomplish the additional work as specified in, 

and as required by, paragraph (2) of this AD.

(4) If, during any SDI as required by paragraph (2) of this AD, any cracks are

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

and within the compliance time(s) specified in these instructions, 

accomplish the repair, including any follow-on actions, as applicable, 

accordingly.

Ref. Publications: Airbus SB A320-57-1013 original issue dated 12 April 1989, or Revision 01 

dated 29 September 1992.

Airbus SB A320-57-1175 original issue dated 24 October 2013, and

Revision 01 [expected end of March 2014].

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 17 January 2014 as PAD 14-013 for consultation 

until 14 February 2014. No comments were received during the 

consultation period.

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.