EASA AD No.: 2013-0226

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0226

Date: 23 September 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 

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 95-099-067 dated 24 May 1995.

ATA 57 Wings – Center Section / Pressurized Floor Fittings at Frame 36

Junction – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A320-211, A320-212 and A320-231 aeroplanes, manufacturer serial 

numbers (MSN) up to 0104 inclusive.

Reason: During center fuselage certification full scale fatigue test, damage was found on 

the pressurized floor fittings at Frame 36, below the lower surface panel. 

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

of the aeroplane.

To prevent such damage, Airbus developed modification 21282, which was 

introduced in production from MSN 0105, to reinforce the pressurized floor 

fitting lower surface by changing material. For affected in-service aeroplanes, 

Airbus issued Service Bulletin (SB) A320-57-1028, introducing repetitive 

inspections, and SB A320-57-1029, which provides modification instructions.

DGAC France issued AD 95-099-067 to require these repetitive inspections

and, depending on findings, corrective action(s), while the modification was 

specified in that AD as optional terminating action for these inspections.

Following new analysis in the frame of ESG (Extended Service Goal) exercise, 

the inspection thresholds and intervals have been revised to meet the original 

DSG (Design Service Goal).

For the reasons described above, this AD retains the requirements of DGAC 

France AD 95-099-067, which is superseded, but requires these actions within 

reduced compliance times.

Effective Date: 07 October 2013
EASA AD No.: 2013-0226

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Initially, within the compliance time defined in Table 1 of this AD, as 

applicable, and thereafter at intervals not to exceed 9 300 flight cycles (FC)

or 18 600 flight hours (FH), whichever occurs first, accomplish a detailed 

inspection of the 6 fittings of the pressurized floor at Frame 36, under lower 

surface panel in accordance with the instructions of Airbus SB A320-57-

1028.

Table 1: Initial Inspection

Compliance time: whichever occurs later, A, B or C

A

Before accumulation of 20 900 FC or 41 800 FH, whichever 

occurs first since aeroplane first flight

B

Within 9 300 FC or 18 600 FH, whichever occurs first since last 

Airbus SB A320-57-1028 inspection

C

Within 1 250 FC or 2 500 FH, whichever occurs first after the 

effective date of this AD, without exceeding 12 000 FC from last 

Airbus SB A320-57-1028 inspection

(2) If, during any inspection as required by paragraph (1) of this AD, damage 

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

and, within the compliance time specified in these instructions, accomplish 

the repair accordingly, including any specified follow-on actions, as 

applicable.

(3) Modification of an aeroplane in accordance with the instructions of Airbus 

SB A320-57-1029 constitutes terminating action for the inspections as 

required by paragraph (1) of this AD for that aeroplane.

Ref. Publications: Airbus SB A320-57-1028 dated 12 August 1991, or Revision 01 dated 19 April 

1996, or Revision 02 dated 03 June 2013.

Airbus SB A320-57-1029 dated 12 August 1991, or Revision 01 dated 10 

November 1992, or Revision 02 dated 16 June 1999.

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 21 August 2013 as PAD 13-124 for consultation 

until 18 September 2013. 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.