EASA AD No.: 20 14

- 0217

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 14

- 0217

Date: 26 September 2014

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: None



### ATA 22, 31 Auto Flight / Instruments

– Stop Rudder Input Warning

– Installation / Activation

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

.
Reason: During design reviews that were conducted following safety recommendations related to in

- service incidents and one accident on another aircraft type , i t has been determined that, in specific flight conditions , the allowable load limit s on the vertical tail plane could be reached and possibly exceeded.
This condition , if not corrected
, could lead , in the worst case, to detachment of the vertical tail plane in flight and consequent loss of the aeroplane

. To prevent such a possibility, Airbus has developed modification s within the flight augmentation computer (F A C) to reduce the vertical tail plane stress and to activate a conditional aural warning within the flight warning computer (FWC) to further protect against pilot induced rudder doublets

. For the reasons describe d above, this AD requ ires installation and activation of the stop rudder input warning (SRIW) logic

. In addition, this AD requires, prior to or concurrent with modification of an aeroplane with the activation of the SRIW, upgrades of the FAC and FWC , to introduce the SRIW logic and SRIW aural capability, respectively. After modification
, th is AD prohibit s installation of certain Part Number (P/N) FWC and FAC.

Effective Date: 10 October 2014EASA AD No.: 20 14

- 0217

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. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 48 months after the effective date of this AD, m odify the pin programming to activate the SRIW logic in accordance with the instruction s of Airbus Ser vice Bulletin (SB) A320

- 22

- 14 80

. (2) Prior to, or concurrent with, modification of an aeroplane as required by para graph (1) of this AD, i dentify the P/N of the FWC and of the FAC install ed on the aeroplane and
, i f the FWC and/ or FAC P/N installed on aeroplane is listed in Table 1 or Table 2 of Appendix 1 of this AD, replace the FWC and /or FAC , as applicable, with a unit having a P/N listed in the Table 3 of Appendix 1 of this AD in accordance with the instructions of Airbus SB A320

- 22

- 1375 (FAC 621 Hard B), or Airbus SB A320

- 22

- 1427 (FAC 622 Hard B), or Airbus SB A320

- 22

- 1461 (FAC 623 Hard B), or Airbus SB A320

- 22

- 1447 (FAC A02 Hard C), as applicable
, and Airbus SB A320

- 31

- 1414 (FWC H2

- F7)

. (3) A n a eroplane on which Airbus modification (mod) 154473 has been embodied in production is compliant with the requirements of paragraphs (1) and (2) of this AD
, provid ed it is determined that no FWC having a P/N listed in Table 1
, and no FAC having a P/N listed in Table 2, respectively
, of Appendix 1 of this AD
, ha s been installed on that aeroplane since Airbus date of manufacture

. If a post

- mod 154473 aeroplane is found to be no longer in the correct configuration, before next flight after the effective date of this AD, restore the aeroplane to its correct configuration as specified in paragraph (2) of this AD. ( 4 ) A fter modificatio n of an aeroplane as required by paragraph (1) of this AD, or restored as required by paragraph (3) of this AD, as applicable, do not install on that aeroplane a FWC having a P/N listed in Table 1
, or a FAC having a P/N listed in Table 2, as applicable, of Appendix 1 of this AD. ( 5 ) Installation of a version (P/N) of the FWC or FAC approved after the effective date of this AD is equal to compliance with the requirements of paragraph (2) or (3) of this AD, provided the conditions as specified in paragraphs (5.1) and (5.2) of this AD are met

. ( 5 .1) The version (P/N) must be approved by EASA
, or approved under Airbus D esign O rganisation A pproval (DOA) ; and (5 .2) The installation must be accomplished in accordance with aeroplane modification instructions approved by EASA , or approved under Airbus DOA

.
Ref. Public ations: Airbus SB A320

- 22

- 1375 original issue dated 15 January 2014

. Airbus SB A320

- 22

- 1427 original issue dated 25 January 2013

. Airbus SB A320

- 22

- 1447 original issue dated 18 October 2013

. Airbus SB A320

- 22

- 1461 original issue dated 31 October 2013

. Airbus SB A320

- 22

- 1480 original issue dated 09 July 2014

. Airbus SB A320

- 31

- 1373 origina l issue dated 28 September 2012. Airbus SB A320

- 31

- 1414 original issue dated 19 December 2012

. 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 23 July 2014 as PAD 14

- 1 19 for consultation until 20 August 2014 . The Comment Response Document can be found at http://ad.easa.europa.eu/

.EASA AD No.: 20 14

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TE. CAP.0011 0

- 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. 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 conte nt 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 14

- 0217

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

Table 1

– FWC P/N non
- compatible with SRIW activation
350E017238484 (H1D1) 350E053020303 (H2E3) 350E016187171 (C5) 350E053020404 (H2E4) 350E017248685 (H1D2) 350E053020606 (H2F2) 350E017251414 (H1E1) 350E053020707 (H2F3) 350E017271616 (H1E2) 350E053021010 (H2F3P) 350E018291818 (H1E3CJ) 350E053020808 (H2F4) 350E018301919 (H1E3P) 350E053020909 (H2

- F5) 350E018312020 (H1E3Q) 350E053021111 (H2

- F6) 350E053020202 (H2E2)



### Table 2

– FAC P/N non
- compatible with SRIW activation

B397AAM0202 B397BAM0101 B397BAM0512 B397AAM0301 B397BAM0202 B397BAM0513 B397AAM0302 B397BAM0203 B397BAM0514 B397AAM0303 B397BAM0305 B397BAM0515 B397AAM0404 B397BAM0406 B397BAM0616 B397AAM0405 B397BAM0407 B397BAM0617 B397AAM0506 B397BAM0507 B397BAM0618 B397AAM0507 B397BAM0508 B397BAM0619 B397AAM0508 B397BAM0509 B397BAM0620 B397AAM0509 B397BAM0510 B397CAM0101
B397AAM0510 B397BAM0511 B397CAM0102 Soft P/N G2856AAA01 installed on h ard P/N C13206AA00



### Table 3

– FWC and FAC minimum compatible with SRIW activation
Aeroplane C onfiguration Required I nstallation All, no sharklet FAC P/N B397BAM0621 (621 hard B)
Sharklet A320 and A319 FAC P/N B397BAM0622 (622 hard B)
Sharklet A321 FAC P/N B397BAM0623 (623 hard B)

All FAC soft P/N G2856AAA02 installed on h ard P/N C13206AA00 (CAA02 hard C) FWC P/N 350E053021212 (H2

- F7)