EASA AD No.: 2013 - 0181R1

TE. CAP.0011 0 - 003 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 13 - 0181 R1

Date: 20 August 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) exempt ion]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s ): A300 and A300 - 600 aeroplane s TCDS Number: France TCDS No

. 145 F oreign AD: Not applicable Revision : This AD revises EASA AD 2013 - 0181 dated 09 August 2013 , which superseded

DGAC France AD 1998 - 449 - 265(B)R1 dated 18 November 1998

. 

### ATA 57 Wings – Outer S hroud B ox H inge B racket – Inspection /

Modification Manufacturer(s): Airbus (forme r ly Airbus Industrie) Applicability: Airbus A300 B2 - 1C, A300B2 - 203, A300B2K - 3C, A300B4 - 103, A300B4 - 120, A300B4 - 203, A300B4 - 2C , A300C4 - 203, and A300F4 - 203 aeroplanes , and A300 B4 - 60 1 , A300B4 - 603, A300B4 - 605R, A300B4 - 620, A300B 4 - 622 and A300C4 - 620 aeroplanes , all manufacturer serial numbers , except aeroplanes that have received AIRBUS modification (mod.) No

. 6661 in production. Reason: In the past , a ft hinge brackets of the ou ter wing box were found cracked. Fracture of a bracket would allow vertical movement of the inner shroud box structure , which could result in damage to the top skin of the inboard flap. In ad dition, the loads carried by the brackets will be transferred to the remaining supports , which may also crack and cause extensive structural damage. This condition, i f not detected and corrected , could affect the structural integrity of the aeroplane. To address this potential unsafe condition, DGAC France issued AD 1998 - 449 - 265(B) (later revised) to require repetitive inspection s of the hinge bracket of the outer box and, depending on findings, corrective action(s)

. Since that AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analysi s were performed in order to substantiate the A300 Extended Service Goal (ESG) and A300 - 600 Extended Service Goal (ESG2) exerci se.EASA AD No.: 2013 - 0181R1

TE. CAP.0011 0 - 003 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. The results of these analyses led to a change in the inspection threshold s and interval s in Flight C ycles (FC) and the introduction of F light H our s (FH) limits

. For the reasons desc r ibed above, this AD retains the requirements of DGAC France AD 1998 - 449 - 265(B)R1 , which is superseded, but requires those actions within the new thresholds and intervals given by A irbus Service Bulletin (SB) A300 - 57 - 0142 Revision 04 or A300 - 57 - 60 10 Revision 05 , as applicable to aeroplane model

. Revision 1 of this AD is issued to add model A300B4 - 203 aeroplanes to the applicability and compliance time tables

. This model is covered by Airbus SB A300 - 57 - 0142 , but was mistakenly omitted from the original AD issue

. Effective Date: Revision 1: 03 September 2013 Original issue: 23 August 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unless previously accomplished: ( 1 ) Within the compliance time indicated in Table 1 of this AD, as applicable to aeroplane model, accomplish a detail visual inspection (DVI) of the forward and aft outer shroud box hinge bracket s in accordance with the instructions of Airbus SB A300 - 57 - 0142 Revision 04 , or SB A300 - 57 - 60 10 Revision 0 5 , as applicable to aeroplane model.

Table 1 : Inspection Threshold s Aeroplanes Compliance time, whichever occurs first since aeroplane first flight A300B4 - 601, A300B4 - 603, A300B4 - 605R, A300B4 - 620, A300B4 - 622 and A300C4 - 620 5 000 FC or 10 400 FH A300 B4 - 2C, A300B4 - 203, A300C 4 - 203, and A300 F4 - 203 A300 B2 - 1C, A300B2 - 203 and A300 B2K - 3C 5 000 FC or 5 400 FH A300B4 - 103 and A300 B4 - 120 5 000 FC or 6 600 FH ( 2 ) Thereafter, at intervals not to exceed the value as indicated in Ta b le 2 of this AD , as applicable to aeroplane model, repeat the inspection in accordance with the instructions of Airbus SB A300 - 57 - 0142 Revision 04 or SB A300 - 57 - 60 10 Revision 05 , as applicable to aeroplane model , or accomplish the replacement of the hinge bracket in accordance with the instruction s of Airbus SB A300 - 57 - 0143 Revision 02 or SB A300 - 57 - 6011 Revision 02 , as appli cable to aeroplane model.

Table 2: Inspection Interval s Aeroplanes Compliance time, whichever occurs first A300B4 - 601, A300B4 - 603, A300B4 - 605R, A300B4 - 620, A300B4 - 622 and A300C4 - 620 1 000 FC or 2 000 FH A300 B4 - 2C, A300B4 - 203, A300C 4 - 203 and A300 F4 - 203 A300 B2 - 1C, A300B2 - 203 and A300 B2K - 3C 1 000 FC or 1 0 00 FH A300B4 - 103 and A300 B4 - 120 1 000 FC or 1 3 00 FHEASA AD No.: 2013 - 0181R1

TE. CAP.0011 0 - 003 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. ( 3 ) If, during any inspection as required by paragraph (1) or ( 2 ) of this AD, a crack less than 8 mm in length is found in one half bracket , at intervals not to exceed the value as indicated in Table 3 of this AD, as applicable to aeroplane model, repeat the inspection in accordance with the instructions of Airbus SB A300 - 57 - 0142 Revision 04 , or SB A300 - 57 - 60 10 Revision 0 5 , as applicable to aeroplane model, or replace the damaged hinge bracket in accordance with the instruction s of Airbus SB A300 - 57 - 0143 Revision 02 , or SB A300 - 57 - 6011 Revision 02 , as applicable to aeroplane model.

Table 3 : Reduced Inspection Interval s after crack ( < 8 mm ) detection Aeroplanes Compliance time, whichever occurs first A300B4 - 601, A300B4 - 603, A300B4 - 605R, A300B4 - 620, A300B4 - 622 and A300C4 - 620 50 FC or 100 FH A300 B4 - 2C, A300B4 - 203, A300C 4 - 203 and A300 F4 - 203 A300 B2 - 1C, A300B2 - 203 and A300 B2K - 3C 50 FC or 50 FH A300B4 - 103 and A300 B4 - 120 50 FC or 65 FH ( 4 ) If, during any inspection as required by paragraph (1) , (2) or ( 3 ) of this AD, a crack of 8 mm in length or more is found , or both half bracket s are cracked , or a hinge bracket is found fractured, before next flight , replace the damaged hinge bracket in accordance with the instructions of Airbus SB A300 - 57 - 0143 Revision 02 , or SB A300 - 57 - 6011 Revision 02 , as applicable to aeroplane model

. ( 5 ) Inspections , accomplished before the effective date of this AD in accordance with the instructions of Airbus SB A300 - 57 - 0142 at original issue up to Revision 03 , or SB A300 - 57 - 60 10 at Revision 01 up to Revision 0 4 , are acceptable to compl y with the requirements of paragraph (1) and ( 2 ) of this AD (initial and repetitive inspection). ( 6 ) Modification of an aeroplane in accordance with the instructions of Airbus SB A300 - 57 - 0143 Revision 02, or SB A300 - 57 - 6011 Revision 02, as applicable to ae roplane model, constitutes terminating action for the initial and repetitive inspections required by paragraph (1), (2) and (3) of this AD

. ( 7 ) Modification of an aeroplane , accomplished before 28 November 1998 (the effective date of DGAC France AD 1998 - 449 - 265(B) at original issue) in accordance with the instructions of Airbus SB A300 - 57 - 0143 at original issue or Revision 01, or SB A300 - 57 - 6011 at original issue or Revision 01, as applicable to aeroplane model, constitutes terminating action for the repetitive inspections required by paragraph (2) and (3) of this AD, provided that, after modification of the aeroplane but before next flight after the effective date of this AD , the aeroplane has successfully passed a one - time DVI of the forward and af t outer shroud box hinge brackets as required by paragraph (1) of this AD. Ref. Public ations: Airbus SB A300 - 57 - 0142 original issue dated 17 December 1986, Revision 01 dated 09 April 1990, Revision 02 dated 16 January 1991 , Revision 03 dated 22 February 1999 , or Revision 04 dated 30 March 2011

. Airbus SB A300 - 57 - 0143 original issue dated 17 December 1986, Revision 01 dated 19 March 1987, or Revision 02 dated 10 July 1989

.EASA AD No.: 2013 - 0181R1

TE. CAP.0011 0 - 003 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. Airbus SB A300 - 57 - 6010 Revision 01 dated 14 December 1990 , Revision 02 dated 30 March 1998, Revision 03 dated 16 September 1998, R evision 04 dated 22 February 1999, or Revision 05 dated 21 February 2011

. Airbus SB A300 - 57 - 6011 original issue dated 17 December 1986, Revision 01 dated 19 March 1987, or Revision 02 dated 10 July 1989

. 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. Th e original issue of th is AD was posted on 07 March 2013 as PAD 13 - 043 for consultation until 04 April 2013

. 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 conte nt of the requirements in this AD, please contact: AI RBUS SAS

– E I AW (Airworthiness Office ) E - mail: continued.airworthiness - wb.external@airbus.com

.