EASA AD No.: 20 13

- 0 220

TE. CAP.0011 0

- 00 3 © 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 13

- 0 220

Date: 1 8 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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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): A300, A300

- 600 and A310 aeroplanes

TCDS Number: France No

. 145

F oreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage

– SRM R epairs on Floor Cross Beam s Flange at Frame 11 and F rame 12A

– Inspection / Repair

Manufacturer(s): Airbus ( formerly Airbus Industrie)
Applicability: Airbus A300 and A310 aeroplanes
, all certified models
, all manufacturer serial numbers (MSN)
, A300

- 600 aeroplanes , all certified models, all MSN, except those on which Airbus modification 12699 has been embodied in production.

Reason: In the frame of the Extended Service Goal (ESG) activity, all existing Structural Repair Manual ( SRM ) repairs were reviewed. This analysis, which consisted in new static and fatigue calculations, revealed that some repairs were no longer applicable to some specific areas. These repairs
, if not reworked
, could affect the structural integrity of the aeroplane. To address the repairs on the floor cross beams flange
, Airbus issued Alert Operator Transmission (AOT) A300

- 53 A 0392, AOT A300

- 53 A 6171 and AOT A310

- 53 A 2135

. To address this unsafe condition , and f urther to the implementation of the Aging Aircraft Safety Rule (AASR) , this A irworthiness D irective requires an inspection of the floor cross beam s flange at fram e ( FR ) 11 an d FR 1 2A to identify SRM repairs and
, depending on findings
, accomplishment of corrective action.

Effective Date: 0 2 October 2013EASA AD No.: 20 13

- 0 220

TE. CAP.0011 0

- 00 3 © 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 3 0 months after the effective date of this AD, accomplish a general visual inspection (GVI) of the floor cross beam s flange located at FR 11 and FR 12 A in accordance with the instructions of Airbus AOT A300

- 53 A 0392
, AOT A300

- 53 A 6171 or AOT A310

- 53 A 2135
, as applicable to aeroplane type , to identify repairs accomplished. A review of maintenance records is acceptable to identify the repairs accomplished on the floor cross beam s flange at FR11 and FR 12 A in lieu of the GVI , provided that the repairs can be posit ively identified from that review. (2) If, during any inspection as required by paragraph ( 1 ) of this AD, any repair is identified as having been previously accomplished in accordance with A300 SRM 53

- 12

- 00 PB701 figures 711, 712 and 713 , or A300

- 600 SRM 53

- 12

- 15 PB201 figures 204, 205 and 206 , or A300

- 600 Freighter SRM 53

- 12

- 15

- C2 PB201 figures 204, 205 and 206 , or A310 SRM 53

- 12

- 15 PB201 figures 204, 205 and 206
, contact Airbus for approved repair instructions and, with in 30 months after the effective date of this AD , accomplish the repair accordingly.

Ref. Public ations: Airbus AOT A300

- 53 A 0392 dated 14 March 2012

. Airbus AOT A300

- 53 A 6171 dated 14 March 2012

. Airbus AOT A310

- 53 A 2135 dated 14 March 2012

. The use of later approv ed 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 31 July 2013 as PAD 13

- 112 for consultation until 28 August 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 SAS

– EIAW (Airworthiness Office), E

- mail: continued.airworthiness

- wb.external@airbus.com

.