EASA AD No.: 2014-0217

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0217

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 accordance 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 operate 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

Foreign 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, it has 

been determined that, in specific flight conditions, the allowable load limits 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 modifications within the 

flight augmentation computer (FAC) 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 described above, this AD requires 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, this AD prohibits installation of certain Part Number (P/N) FWC

and FAC.

Effective Date: 10 October 2014
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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 48 months after the effective date of this AD, modify the pin 

programming to activate the SRIW logic in accordance with the instructions

of Airbus Service Bulletin (SB) A320-22-1480.

(2) Prior to, or concurrent with, modification of an aeroplane as required by 

paragraph (1) of this AD, identify the P/N of the FWC and of the FAC 

installed on the aeroplane and, if 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) An aeroplane on which Airbus modification (mod) 154473 has been 

embodied in production is compliant with the requirements of paragraphs 

(1) and (2) of this AD, provided 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, has 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) After modification 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 Design Organisation Approval (DOA); and

(5.2) The installation must be accomplished in accordance with aeroplane 

modification instructions approved by EASA, or approved under 

Airbus DOA.

Ref. Publications: 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 original 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 14-119 for consultation until 

20 August 2014. The Comment Response Document can be found at 

http://ad.easa.europa.eu/.
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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.
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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 hard P/N C13206AA00

Table 3 – FWC and FAC minimum compatible with SRIW activation

Aeroplane Configuration Required Installation

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 hard 

P/N C13206AA00 (CAA02 hard C)

FWC P/N 350E053021212 (H2-F7)