EASA AD No : 2012-0012 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0012 

Date: 23 January 2012 

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 EC 1702/2003, Part 21A.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]. 

Type 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 27 Flight Controls – Flap Interconnecting Strut – Identification / 

Modification / Replacement 

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, A320-111, 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: The flap interconnecting strut is a safety device of the High Lift System which 

acts as an alternative load path from one flap surface to another in case of a 

flap drive system disconnection. In such a failure case, the installed proximity 

sensors provide information to the slat flap control computer (SFCC) and the 

operation of the flap drive system is inhibited. 

A recent engineering investigation has shown that, when a certain combination 

of target/sensor serial number (s/n) is installed on a flap interconnecting strut, a 

"target FAR" signal cannot be detected when reaching the mechanical end stop 

of the interconnecting strut. 

This condition, if not corrected, could cause a flap down drive disconnection to 

remain undetected, due to an already-failed interconnecting strut sensor, 

potentially resulting in asymmetric flap panel movement and consequent loss of 

control of the aeroplane. 

For the reason described above, this AD requires the identification and 

replacement of struts that have a certain target/sensor s/n combination 

installed. 

Effective Date: 06 February 2012 
EASA AD No : 2012-0012 

EASA Form 110 Page 2/3 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished : 

(1) Within 8 000 flight hours (FH) after the effective date of this AD, accomplish 

the following actions in accordance with the instructions of Airbus Service 

Bulletin (SB) A320-27-1206 Revision 01: 

(1.1) Determine the Part Number (P/N) of the Interconnecting Struts 

installed on both left-hand (LH) and right-hand (RH) wings on the 

aeroplane. 

(1.2) If an interconnecting strut is installed with a P/N as listed in Table 1 

of this AD, identify the P/N and the s/n of the associated target and 

proximity sensor and, for the target and proximity sensor P/N and 

s/n combination as defined in Appendix 1 of this AD, within the 

compliance times defined in Appendix 1 of this AD, carry out the 

actions specified in Appendix 1 of this AD for that interconnecting 

strut 

Table 1 

Interconnecting Strut Part Numbers: 

D 575-70305-000-00 

D 575-70305-001-00 

D 575-70305-002-00 

D 575-70305-006-00 

D 575-70305-008-00 

D 575-70305-010-00 

D 575-70305-012-00 

D 575-70322-000-00 

(1.3) A review of aeroplane maintenance records is acceptable to 

determine the P/N of the installed interconnecting struts and/or the 

P/N and s/n of the associated target and proximity sensor, in lieu of 

the instructions of Airbus SB A320-27-1206 revision 01, if the P/N of 

the installed interconnecting struts and the P/N and the s/n of the 

associated target and proximity sensor can be conclusively identified 

from that review. 

(2) Aeroplanes on which Airbus modification (mod) 27956 has been embodied 

in production, and on which no interconnecting strut replacement with a 

strut with a P/N as identified in Table 1 of this AD has been made since first 

flight, are not affected by the requirements of paragraph (1) of this AD. 

(3) For aeroplanes that have already been inspected, prior to the effective date 

of this AD, in accordance with the instructions of Airbus SB A320-27-1206 

at original issue, within the compliance time defined in paragraph (1) of this 

AD, accomplish the additional work as defined in Airbus SB A320-27-1206 

at Revision 01, unless a review of aeroplane maintenance records can 

conclusively determine that no interconnecting strut P/N D 575-70305-010-

00 or P/N D 575-70305-012-00 is installed. 

(4) From the effective date of this AD, do not install or modify an 

interconnecting strut with a P/N as identified in Table 1 of this AD on an 

aeroplane, unless it has been determined to be in compliance with the 

requirements of this AD. 

Ref. Publications: Airbus SB A320-27-1206 Revision 01 dated 10 October 2011. 

The use of later approved revisions of this 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. 
EASA AD No : 2012-0012 

EASA Form 110 Page 3/3 

2. This AD was posted on 25 February 2011 as PAD 11-025 for consultation 

until 25 March 2011 and republished on 28 November as PAD 11-025R1 for 

additional consultation until 12 December 2011. 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 

this AD, please contact: AIRBUS – Airworthiness Office – EAS, 

Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com. 

Appendix 1 – Action(s) and Compliance Time(s) for 

Targets P/N ABS0121-13 and P/N 8-536-01

Configuration / condition Action and Compliance time 

Target serial 

number 

Proximity sensor P/N and s/n 

s/n is lower than 

1600, or s/n 

unreadable 

P/N ABS0121-31 

or P/N 8-372-04 

s/n between 

C59198 and 

C59435, or s/n 

C500000 or higher 

Before next flight (see exception in Note 1

below), replace the interconnecting strut 

with a serviceable unit (see Note 2 below) 

in accordance with the instructions of 

Airbus SB A320-27-1206 Revision 01. 

s/n is 1600 or 

higher All P/N All s/n 

Within 8 000 FH after the effective date of 

this AD, re-identify the interconnecting 

strut in accordance with the instructions of 

Airbus SB A320-27-1206 Revision 01. 

Note 1: If the interconnecting strut cannot be replaced, before next flight, inspect the flap down drive in 

accordance with the instructions of Airbus SB A320-27-1206 Revision 01 and, if no discrepancy 

is found, within 50 flight cycles after the inspection, replace the interconnecting strut with a 

serviceable unit (see Note 2 below). If discrepancies are detected during the inspection, the 

replacement must be accomplished before next flight. 

Note 2: For the purpose of this AD, a serviceable interconnecting strut is a unit which has been 

determined to be in compliance with the requirements of this AD.