EASA AD No.: 20 15

- 0170

TE. CAP.0011 0

- 00 4 © 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
. : 2015 - 0 1 70

Date: 18 August 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): A318, A319, A320 and A321 aeroplanes
TCDS Number: EASA.A.064
F oreign AD: Not applicable Supersedure: None



### ATA 92 Electric and Electronic Common Installation
– Cockpit Panel Bracket
– Inspection
Manufacturer(s): Airbus (formerly Airbus Industrie) Applicability: Airbus A318

- 111, A318

- 112, A318

- 121, A318

- 122, A319

- 111, A319

- 112, A319

- 113, A319

- 114, A319

- 115, A319

- 131, A319

- 132, A319

- 133, A320

- 211, A320

- 212, A320

- 214, A320

- 215, A320

- 216, A320

- 231, A320

- 232, A320

- 233, A321

- 111, A321

- 112, A321

- 131, A321

- 211, A321

- 212, A321

- 213, A321

- 231 and A321

- 232 aeroplanes, all manufacturer serial numbers , except those on which Airbus modification (mod) 35869 has been embodied in production.
Reason: During an unscheduled maintenance operation on an A330 aeroplane , the 10VU rack was removed for access a nd cracks were discovered on 10 VU rack side fittings on lugs 1, 3 and 4. A s a similar design is installed on A320 family aeroplanes, a sampling review was done to determine the possible fleet impact. The result showed that s everal aeroplanes had cracked or broken 10VU rack side fittings. This condition, if not detected and corrected , could lead to a high vibration level on the primary flight

- and navigation displays during critical flight phases ( take

o ff and la nding) , possibly creating reading difficulties for the crew. Prompted by these findings , Airbus developed mod 35869 to reinforce the affected rack fitting lug s. For in

- service aeroplanes , Airbus published Service Bulletin (SB) A320

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- 1087 to provide inspection and repair instructions

. For the reason s describe d above, this AD requ ires repetitive detailed inspection s (DET) of the affected 10VU rack fitting lug s and, depending on findings, accomplishment of a repair.
Effective Date: 0 1 September 2015EASA AD No.: 20 15

- 0170

TE. CAP.0011 0

- 00 4 © 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 the compliance time d efine d in Table 1 of this AD , and , thereafter , at interval s not to exceed 20 000 f light c ycles (FC) or 40 000 f light h ours (FH), whichever occurs first, accomplish a DET of the 10VU lugs in accordance with the instructions of Airbus SB A320

- 92

- 1087

.

Table 1

– Initial Inspection Compliance T ime (whichever occurs later , A or B )
A Before exceeding 30 000 FC or 60 000 FH, whichever occurs first since aeroplane first flight B Within 24 months after the effective date of this AD (2) If, during any DET as required by paragraph (1) of this AD , any crack is found, within the applicable compliance time as defined in p aragraph 1.E.(2) of Airbus SB A320

- 92

- 1087, accomplish the applicable corrective actions in accordance with the instructions of Ai rbus SB A320

- 92

- 1087. (3) Repair of the 10VU rack lugs on an aeroplane, a s required by paragraph (2) of this AD , does not constitute terminating action for the repetitive D ET as required by paragraph (1) of this AD for that aeroplane

. (4) Within 9 0 days after each DET as required by paragraph (1) of this AD , report the results (including no findings) to Airbus.

Ref. Public ations: Airbus SB A320

- 92

- 1087 o riginal issue dated 28 March 2011, or Revision 01 dated 17 May 2011, or Revision 02 dated 25 November 2014

. The use of later approved revisions of th i s document 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 06 July 2015 as PAD 15

- 0 90 for consultation until 03 August 2015 . 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, Certification 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

.