EASA AD No.: 20 15

- 0088 R1

TE. CAP.0011 0

- 00 4 © 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 15

- 0088 R1

Date: 0 2 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 accordan ce 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 requirements 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) exemp tion]. 

### 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

Revision : This AD revises EASA AD 2015

- 0088 dated 22 May 2015 , which cancel led DGAC

France AD 95

- 203

- 072 dated 11 October 1995 ; and supersede d DGAC France AD 2 001

- 508 dated 17 October 2001

, and AD F

- 2004

- 147 (EASA approval ref. 2004

- 8601 ) dated 18 August 2004.



### ATA 27 Flight Controls

– Elevator Aileron Computer s

– Re placement /

Software Update

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, A32 1

- 211, A321

- 212, A321

- 213, A321

- 231 and A321

- 232 aeroplanes, all manufacturer serial numbers (MSN)

.

Reason: T he latest e levator a ileron c omputer ( ELAC ) standard, L97+

, implement s enhanced Angle of Attack (AOA) monitoring in or der to better detect cases of AO A blockage , including multiple AO A blockage

. Two ELAC L97+ versions are currently available , Part Number ( P/N ) 3945129109 with data loading capability

, and P/N 3945128215 without the data loading capability. Three existing ADs requiring installation of earlier ELAC (software) have been identified and taken into account for cancellation by this new AD.

For the rea son s describe d above, EASA issued AD 2015

- 0088

, cancel ling DGAC France AD 95

- 203

- 072 (no requirements retained) , and partially retain ing the requirements of DGAC France AD 2001

- 508, and AD F

- 2004

- 147 (EASA approval ref. 2004

- 8601)

, which we re superseded, and to require replacement of all ELAC with ELAC L97+ standard.
Since that AD was issued, some errors were detected in Appendix 1 of the AD , and one P/N ELAC was inadvertently omitted

. This AD revises EASA AD 2015

- 0088 to correct these erro r s and to add clarification to paragraph (7).EASA AD No.: 20 15

- 0088 R1

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: Revision 1: 09 June 2015 Original issue: 01 June 2015

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:

Restatement of (part of) the requirements of DGAC France AD 2001

- 508 : (1) For certain A319 and A320 aeroplanes

, as identified by MSN in Airbus Service Bulletin (SB) A320

- 27

- 1135

, b efore 31 December 2002, replace all ELAC L80 units with ELAC L81 standard units in accordance with the instruction s of Airbus SB A320

- 27

- 1135.

Restatement of (part of) the requirements of DGAC France AD F

- 2004

- 147 : (2) For certain A321 aeroplanes

, as identified by MSN in Airbus SB A320

- 27

- 115 1 or SB A320

- 27

- 1152

, b efore 31 December 2005, install ELAC L83 or L91 software, in accordance with the instruction s of Airbus SB A320

- 27

- 1151 or Airbus SB A320

- 27

- 1152 , as applicable

.

New requirements of this AD : (3) Within the compliance time as defined in Table 1 of this AD, as applicable, replace each ELAC unit with an ELAC L97+ P/N 39451291 00 unit with software P/N 39451291 09 , or modify ELAC unit s in to ELAC P/N 3945129100 unit s with L97+ operational software P/N 394512910 9 loaded, in accordance with the instruction s of Airbus SB A320

- 27

- 1243

.

Table 1

– ELAC L97+ Installation

Aeroplanes (all models) Compliance Time

(after 01 June 2015, the effective date of the or i ginal issue of this AD)

A318 and A321 with UTAS AOA (see Note 1 ) 5 months

A319 and A320 with UTAS AOA (see Note 1 ) 10 months

All o ther aeroplane s 2 5 months

Note 1 : Aeroplanes with UTAS (formerly Goodrich) AOA P/N 08 6 1ED or P/N 08 6 1ED2 in stalled in all 3 positions (Captain, First Officer and Standby).

(4) Modification of an aeroplane by r e placing existing ELAC units with ELAC L97+ PN 3945128215 units (see Note 2) in accordance with the instruction s of Airbus SB A320

- 27

- 1244 is an acceptable me thod of compliance with the requirement of paragraph (3) o f this AD for that aeroplane.

Note 2: The Non

- Data

- loadable ELACs L97+ PN 3945128215 are fully

interchangeable and mixable with Data

- loadable ELAC L97+ PN 3945129100 with operational software P / N 3945129109 loaded.

(5) A n a eroplane with Airbus mod 156546 (installation of ELAC L97+ with software P/N 3945129109) embodied in production is not affected by the requirements of paragraphs (1) through ( 4 ) of this AD , provide d it is determined that no ELAC having a P/N as listed in A ppendix 1 of this AD has been installed on that aeroplane since its date of manufacture

.EASA AD No.: 20 15

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- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. ( 6 ) Installation of a version (P/N) of an ELAC unit approved after 01 June 2015 [ the effective date of the original issue of this AD ] is equal to compliance with the requirements of paragraph ( 3 ) or ( 4 ) of this AD, provided the conditions as specified in paragraphs ( 6 .1 ) and ( 6 .2) of this AD are met.
( 6 .1) The version (P/N) must be approved by EASA, or approved under Airbus Design Organisation Approval (DOA); and
( 6 .2) The installation must be accomplished in accordance with aeroplane modification instructions approved by EASA , or approved under Airbus DOA.

( 7 ) Do not install on any aeroplane an ELAC unit having a P/N as listed in Appendix 1 of this AD, as required by paragraph ( 7 .1) or ( 7 .2) of this AD, as applicable , except as specified in paragraph (7.3) of this AD

. ( 7 .1) For an aeroplane that, on 01 June 2015 [ the effective date of the original issue of this AD ] , has an ELAC unit installed having a P/N as listed in Appendix 1 of this AD: After modification of that aeroplane as required by paragraph (3) of this AD.
( 7 .2) For an aeroplane that, on 0 1 June 2015 [ the effective date of the original issue of this AD ] , do es not have an ELAC unit installed, having a P/N as listed in Appendix 1 of this AD: From 01 June 2015 [ the effective date of the original issue of this AD ]

. (7.3) I t is allowed to install a data

- l oad able ELAC B unit (P/Ns identified in Appendix 1 of this AD) , provided that, before next flight after installation, or , for aeroplanes not yet modified as required by paragraph ( 3 ) of this AD

, within the applicable compliance time as specified in Table 1 of this AD, L97+ operational software P/N 394512910 9 is uploaded (or later software

– see paragraph (6) of this AD )

.

Ref. Public ations: Airbus SB A320

- 27

- 1135 original issue dated 29 June 2001

, or Revision 01 dated 31 August 2001, or Revision 02 dated 18 April 2002

. Airbus SB A320

- 27

- 1151 original issue dated 09 March 2004

, or Revision 01 dated 19 October 2004

. Airbus SB A320

- 27

- 1152 original issue dated 04 June 2004

, or Revision 01 dated 19 October 200 4, or Revision 02 dated 04 April 2006

. Airbus SB A320

- 27

- 1243 original issue dated 17 M arch 2015

. Airbus SB A320

- 27

- 1244 original issue dated 05 March 2015

. 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. Th e original issue of th is AD was posted on 10 April 2015 as PAD 15

- 03 7 for consultation until 08 May 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

.EASA AD No.: 20 15

- 0088 R1

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

### Appendix 1

– No longer to be installed ELAC

P /N Designation FIN

3945122202 ELAC A320

- 111 Type Def

. 2 CE 1 / 2

3945122203 ELAC L50C 2 CE 1 / 2

3945122303 ELAC L50C 2 CE 1 / 2

3945122304 ELAC L60 2 CE 1 / 2

3945122305 ELAC L61B 2 CE 1 / 2

3945122306 ELAC L61F 2 CE 1 / 2

3945122307 ELAC L62C 2 CE 1 / 2

C12370AA01 ELAC L68C 2 CE 1 / 2

3945122501 ELAC L69 2 CE 1 / 2

3945122502 ELAC L69J 2 CE 1 / 2

3945122503 ELAC L77 2 CE 1 / 2

3945122504 ELAC L78 2 CE 1 / 2

3945122505 ELAC A L80 2 CE 1 / 2

3945123505 ELAC A’ L80 2 CE 1 / 2

3945128101 ELAC B L80 2 CE 1 / 2

3945122506 ELAC A L81 2 CE 1 / 2

3945123506 ELAC A’ L81 2 CE 1 / 2

3945128102 ELAC B L81 2 CE 1 / 2

3945122507 ELAC A L82 2 CE 1 / 2

3945123507 ELAC A’ L82 2 CE 1 / 2

3945128103 ELAC B L82 2 CE 1 / 2

3945122608 ELAC A L83 2 CE 1 / 2

3945123608 ELAC A’ L83 2 CE 1 / 2

3945122609 ELAC A L84 2 CE 1 / 2

3945123609 ELAC A’ L84 2 CE 1 / 2

3945128204 ELAC B L90L 2 CE 1 / 2

3945128205 ELAC B L90N 2 CE 1 / 2

3945128206 ELAC B L91 2 CE 1 / 2

3945129101 ELAC B L91 data load able 2 CE 1 / 2 SW1

3945128207 ELAC B L92 2 CE 1 / 2

3945128208 ELAC B L92L 2 CE 1 / 2

3945128209 ELAC B L93 2 CE 1 / 2

3945129103 ELAC B L93 data load able 2 CE 1 / 2 SW1

3945128210 ELAC B L94 2 CE 1 / 2

3945129104 ELAC B L94 data load able 2 CE 1 / 2 SW1

3945128212 ELAC B L96 2 CE 1 / 2

3945129106 ELAC B L96 data load able 2 CE 1 / 2 SW1

3945129107 ELAC B L96 H

- A data load able 2 CE 1 / 2 SW1

3945128214 ELAC B L97 2 CE 1 / 2

3945129108 ELAC B L97 data load able 2 CE 1 / 2 SW1