E ASA AD No.: 20 13

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- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 1 3 - 0 20 2

Date: 05 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 accordan ce 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 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): A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable Supersedure: This AD supersedes EASA AD 2011

- 0202 dated 13 October 2011

.



### ATA 32 Landing Gear
– Landing Gear Control and Interface Unit Wiring
– Modification
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 , A 320

- 111 , 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

. Reason: After a push back from the gate, an A320 aeroplane was preparing to initiate taxi, when an uncommanded nose landing gear (NLG) retraction occurred, causing the nose of the aeroplane to hit the ground. Investigations revealed that the retraction was caused by a combination of a power interruption to Landing Gear Control and Interface Units ( LGCI U ) and an internal hydraulic leak through the landing gear (LG) selector valve 40GA. Deeper investigations have revealed that LGCIU power interruption appears during engine start at each flight. Even though no incident has been reported in service, it has been determined that a non

- compliance to the safety objective exists when combined with a dormant single failure of the selector valve seal leaking. This condition, if not corrected, could lead to further incidents of untimely unlocking and/or retraction of the NLG which, while on the ground, could result in injury to ground personnel and damage to the aeroplane

. To address the possible hydraulic leak of the LG selector valve, EASA issued AD 2007

- 0065, currently at Revision 2.E ASA AD No.: 20 13

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- Internet/Intranet. To address the risk of untimely unlocking and/or retraction of the NLG , EASA issued AD 2011

- 0202 to require installation of a power interruption protection circuit to the LGCIU and accomplishment of associated modifications. Since that AD was issued, it has been discovered that additional work is necessary to adequately correct this unsafe condition and consequently, Airbus issued Service Bulletin (SB) A320

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- 1346 to Revision 05. An update of the maintenance program me is required as well , following the required modification. For the reason described above, this AD retains the requirements of EASA AD 2011

- 0202 , which is superseded, and requires certain additional actions, as defined in the revised Airbus SB , as applicable to aeroplane model , and an update of the approved mainte nance program me

. Effective Date: 19 September 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the compliance time as specified in Table 1 of this AD, as applicable to aeroplane configuration , modify the aeroplane in accordance with the instructions of Airbus SB A320

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- 1346 Revision 05 or, for Corporate Jet (A319CJ) aeroplanes, in accordance with the instructions of Airbus SB A320

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- 1349 Revision 03, as applicable to aeroplane model.
Table 1 Aeroplane Configuration Compliance time ( after 27 October 2011 , the effective date of EASA AD 2011

- 0202 ) Aeroplanes fitted with LG selector valves having P art Number (P/N) 114079019

- modified in accordance with Airbus modification (mod) 38947 in production, or in accordance with Airbus SB A320

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- 1348 in

- service Within 72 months Aeroplanes fitted with LG selector valves 40GA , having a P/N as listed in Table 2 of this AD, provided the valves have the marking "DI" or “DI

- BE” rec orded on their amendment plates

. All other aeroplanes Within 60 months

Table 2

– LG Selector Valve s 40GA

– list of P/N 114079001 114079001A 114079001AB 114079005 114079005A 114079005AB 114079009 114079009A 114079009AB 114079013 114079015 114079017

(2) For aeroplanes that have already been modified, before the effective date of this AD , in accordance with the instructions of Airbus SB A320

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- 1346 at original issue or Revision 01, or Revision 02, or Revision 03, or Revision 04 , within 72 months after the effective date of this AD , accomplish the actions identified as ‘additional work’ in accordance with the instructions of Airbus SB A3 20

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- 1346 Revision 05

.E ASA AD No.: 20 13

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- Internet/Intranet. (3) A319 Corporate Jet aeroplanes that have already been modified , before the effective date of this AD , in accordance with the instructions of Airbus SB A320

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- 1349 at o riginal issue , or Revision 01, or Revision 02 , are compliant with the requirements of paragraph ( 1) of this AD. ( 4 ) Aeroplanes on which Airbus mod 37866 has been embodied in production are not affected by the requirement s of paragraph s (1) and (2) of this AD. ( 5 ) After having complied with paragraph (1) , (2) , (3) or (4) of this AD , as applicable, update the approved maintenance program me by incorporating the Maintenance Review Board Report task 32.30.00 17 FUNCTIONAL CHECK OF LGCIU POWER SUPPLY RELAYS

. Ref. Public ations: Airbus SB A320

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- 1346 o riginal issue dated 04 December 2008, or Revision 01 dated 27 October 2009, or Revision 02 dated 04 November 2009, or Revision 03 dated 07 January 201 0, or Revision 04 dated 22 April 2011, or Revision 0 5 dated 13 January 201 2

. Ai rbus SB A320

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- 1349 o riginal issue dated 04 December 2008, or Revision 01 dated 31 August 2009, or Revision 02 dated 16 June 2010, or Revision 03 dated 05 October 201 1

. 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 1 9 June 201 3 as PAD 1 3

- 082 for consultation until 17 Ju ly 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 content of the requirements in th is AD, please contact: AIRBUS

- Airworthiness Office

- EIAS, F ax : +33 5 61 93 44 51, E

- mail: account.airworth

- eas@airbus.com

.