EASA AD No.: 20 15
- 0 101 R1

TE. CAP.0011 0
- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 15 - 0 101 R1

Date: 12 June 2015
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 EU 1321/2014 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 [EU 1321/2014 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): A330 and A340
- 200/
- 300 aeroplanes
TCDS Number: EASA A.004, EASA A.015
F oreign AD: Not applicable
Revision : This AD revises EASA AD 2015
- 0101 , dated 03 June 2015

.


### ATA 53 Fuselage – Skin and Structure / Allowable Damage Limits – Records

Check / Repair Manufacturer(s): Airbus (formerly Airbus Industrie) Applicability: Airbus A330
- 201, A330
- 202, A330
- 203, A330
- 223, A330
- 243, [deleted] ,

A330
- 301, A330
- 302, A330
- 303, A330
- 321, A330
- 322, A330
- 323, A330
- 341, A330
- 342 and A330
- 343 aeroplanes, Airbus A340
- 211, A340
- 212 , A340
- 213, A340
- 311, A340
- 312 and A340
- 313 aeroplanes, all manufacturer serial numbers (MSN) up to MSN 1 600 inclusive

. Reason: R esult of a fleet survey accomplished in 200 8 identified that the nature of flight

mission s of A330 and A340
- 200/300 fleets had significantly changed in compar ison with assum ed us ag e during the type certification . Consequently, it was decided to recalculate the Structural Repair Manual (SRM) fatigue values to ensure that the given threshold and intervals remain valid. The results of this recalculation identified reduc ed thresholds and intervals applicable for repairs and Allowable Damage Limit s (ADL) affecting the following areas:

- D oor cut - out corners of door surrounding panels (forward cargo door, forward passenger ( PAX ) door, m id PAX door, emergency exit door/PAX door 3, a ft cargo door, bulk cargo door, a ft PAX door), on both L eft H and (L H ) and R ight H and (RH) sides ,

- Stringer ( STGR ) 9 junction between Frame ( FR ) 10 and FR13 on both LH and RH sides , andEASA AD No.: 20 15
- 0 101 R1

TE. CAP.0011 0
- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. - Fuselage skin doubler repairs on both LH and RH sides

. Failing to apply the reduced thresholds and intervals, could adversely affect the structural integrity of the aeroplane. To address this unsafe condition, Airbus issued SRM revision dated April 2013 and temporary revision (TR) 53
- 001 for the STGR9 junction between FR10 and FR13 area (and subsequent revisions) to introduce reduced thresholds and intervals for the affected ADLs and repairs and issued a set of Service Bulletins (SB) to identify the ADLs used and repairs made, as well as to enable operators to update aeroplane repair records

. Consequently EASA issued AD 2015
- 0101, to requir e identification of any repairs and/or ADL used to assess or control any structural damage on certain structural areas and, depending on findings, accomplishment of corrective action (s)

. Since that AD was issued, data review confirmed that A330 freighter version s are not affected by the un safe condition

. This AD is revise d to remove A330
- 223F and A33 0
- 24 3 F from the A pplicability. Effective Date: Revision 01: 17 June 2015

Original issue: 17 June 2015 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the compliance time defined in Appendix 1 of this AD , as applicable, review the aeroplane maintenance records to identify any SRM ADL used to assess or control a ny structural damage and/ or any structural repair accomplished in accordance with a SRM, as applicable, that have been applied on the areas as specified in Table 1 of this AD.

Table 1

– Affected Areas and Airbus SBs Areas ( on both LH and RH sides ) ( in accordance with the instructions of ) Airbus SB ( as applicable to aeroplane type ) D oor cut - out corners of door surrounding panels (forward cargo door, m id PAX door, emergency exit door/PAX door 3, a ft cargo door, bulk cargo door, a ft PAX door) SB A330
- 53
- 3232 or SB A340
- 53
- 4222
Forward PAX door surround panels SB A330
- 53
- 323 3 or SB A340
- 53
- 422 3 Fuselage Skin Doubler repairs SB A330
- 53
- 323 4 or SB A340
- 53
- 422 4 STGR9 junction between FR10 and FR13 SB A330
- 53
- 323 5 Revision 1 (or any later revision) or SB A340
- 53
- 422 5 Revision 1 (or any

later revision)

Note 1 : F or Airbus SB A330
- 53
- 323 5 and SB A340
- 53
- 422 5, mistake s have been made in these documents at original issue and they therefore cannot be used for compliance with the requirements of this AD.EASA AD No.: 20 15
- 0 101 R1

TE. CAP.0011 0
- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. (2) If, during the review, as required by paragraph (1) of this AD, it has been determined that a SRM ADL was used on an area specified in Table 1 of this AD to assess or control any structural damage , and/ or any structural repair of an area specified in Table 1 of this AD was accomplished in accordance with the instructions of a ny SRM revision or SRM TR , except those specified in Table 2 of this AD (or any later approved SRM or SRM TR revisions) , depending on aeroplane configuration and within the compliance time defined in Appendix 1 of this AD, accomplish action (2.1) or (2.2) of this AD, in accordance with the instr uctions of applicable Airbus SB, as applicable

.

Table 2

– Acceptable SRM / SRM TR Affected aeroplanes Aeroplane areas Airbus SRM All MSN up to MSN 1 444 inclusive All areas , except STGR9 junction between FR10 and FR13 area SRM revision dated April 2013 All MSN up to MSN 1 600 inclusive STGR9 junction between FR10 and FR13 area only SRM TR 53
- 001 dated 28 Nov ember 2014 (2.1) Update the aeroplane repair records with the revised thresholds and intervals , as applicable for the identified structural repairs embodied on the aeroplane in accordance with Airbus SRM as identified in Table 2 of this AD, or later approved (temporary) revisions and , following that update, ac compl ish all updated inspection instructions accordingly

. (2.2) For a repair that was allowed in a previous Airbus SRM and is no longer allowed in the current Airbus SRM , as identified in Table 2 of this AD, c ontact Airbus for specific assessment and approved instructions and within the compliance time specified in those ins tructions, accomplish those instructions accordingly

. ( 3 ) From the effective date of this AD, any structural damage in the areas identified in Table 1 of this AD, must be assessed and , if outside the ADL , corrected (repair or replacement) in accordance with data approved by EASA or Airbus , valid at the time of the (planned) repair or replacement , or Airbus SRM as identified in Table 2 of this AD, or later approved (temporary) revisions

. Ref. Public ations: Airbus SB A330
- 53
- 3232 original issue dated 04 November 2014

.

Airbus SB A340
- 53
- 4222 original issue dated 25 November 2014

. Airbus SB A330
- 53
- 3233 original issue dated 26 September 2014

. Airbus SB A340
- 53
- 4223 original issue dated 26 September 2014

. Airbus SB A330
- 53
- 3234 original issue dated 08 December 2014

. Airbus SB A340
- 53
- 4224 original issue dated 15 December 2014 Airbus SB A330
- 53
- 3235 R evision 0 1 dated 14 January 2015

. Airbus SB A340
- 53
- 4225 R evision 0 1 dated 14 January 2015

. Airbus SRM dated April 2013

. Airbus SRM TR 53
- 001 dated 28 November 2014

. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.EASA AD No.: 20 15
- 0 101 R1

TE. CAP.0011 0
- 00 4 © European Aviation Safety Agency. All rights reserved. 4 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. 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 26 February 2 015 as PAD 1 5
- 017 for consultation until 26 March 2015 . The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD sho uld be referred to the Safety Information Section, Certification 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: AIRBUS

– Airworthiness Office

– EAL. E
- mail: airworthiness.A330
- A340@airbus.com

.EASA AD No.: 20 15
- 0 101 R1

TE. CAP.0011 0
- 00 4 © European Aviation Safety Agency. All rights reserved. 5 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet.



### Appendix 1

– Affected Areas , Compliance Times and Airbus SBs A ffected a eroplane s and configuration ADL location/Repair Compliance Time (after 17 June 2015, [ the effective date of the original issue of this AD ] ) Airbus SB

A330
- 200 Pre
- mod 49144 Mid PAX door surround panels 12 months

SB A330
- 53
- 3232 or SB A340
- 53
- 4222 A330
- 2 00 Pre
- mod 49144 F orward cargo door, emergency exit

door/PAX door 3, aft cargo door, bulk cargo door, and aft PAX door surround panels 24 months A330
- 300 Pre
- mod 49144 A340
- 200/
- 300 pre
mod 49144 Mid PAX door surround panels, forward

cargo door, emergency exit door/PAX door 3, aft cargo door, bulk cargo door, and aft PAX door surround panels

All, Post
- mod 40347 Forward PAX door surround panels For ADL with a Temporary Life Limit: 12 months SB A330
- 53
- 3233 or SB A340
- 53
- 4223 For ADL with a Permanent Acceptance : 24 months
All STGR9 junction between FR10 and FR13 12 months SB A330
- 53
- 3235 Revision 1 or SB A340
- 53
- 4225 Revision 1 A340
- 200/
- 300 Weight Variant ( WV ) 00s Forward and rear fuselage 12 months

SB A330
- 53
- 3234 or SB A340
- 53
- 4224 A340
- 200/
- 300 WV00s Nose forward and centre fuselage

24 months A330
- 200 /
- 300 pre MOD 49144 and A340
- 200 /
- 300 WV20s Forward and rear fuselage, nose forward

and centre fuselage A330
- 200 /
- 300 post - MOD 49144 and A340
- 200 /
- 300 post - MOD 49144 N ose forward and centre fuselage