EASA AD No.: 2012-0082

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0082

Date: 15 May 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD unless otherwis e 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, A rticle 14(4) exemption].


### Design Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A330 and A340 aeroplanes

TCDS Numbers: EASA.A.004, EASA.A.015

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2010-0267 D ated 21 December 2010.



### ATA 27 Flight Controls – Wing Tip Brakes – Operatio nal Test/Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, A330-341, A330-342 and A330-343 aeroplanes, all man ufacturer serial numbers (MSN).
Airbus A340-211, A340-212, A340-213, A340-311, A340 -312, A340-313, A340- 541, A340-542, A340-642 and A340-643 aeroplanes, al l MSN.

Reason: Several wing tip brakes (WTB) have lost the ir braking function in service. Inspection by the manufacturer of these units revea led that the drive shaft was found free to rotate and the braking discs worn. In vestigations are still on-going to determine the exact root cause. The WTB is a Pressure-Off-Brake (POB) with a multi- plate friction device operated by a spring pack. In operation, the brakes are released by dual hydraulic pistons controlled by electro-hydraulic s olenoid valves, energized by the Slat Flap Control Computers (SFCC). The purpose of the WTBs (4 per aeroplane) is to stop and hold the mechanical trans mission in position in some specific failure cases. In such cases, the SFCCs de -energize their WTB solenoids, which remove the hydraulic pressure and lead to the application of the brakes.
This condition, if not detected and corrected, coul d, in some specific failure cases, result in loss of control of the aeroplane. For the reasons described above, EASA issued AD 201 0-0267 to require a one-EASA AD No.: 2012-0082

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. time Operational Test of the WTB/POB performance on the flap and slat systems to detect any dormant failure and, dependin g on findings, applicable corrective actions. This AD also required the repor ting of findings, including none, to the TC holder. Since issuance of EASA AD 2010-0267, additional occ urrences have been reported. The results of the investigations reveale d that WTB fitted with brake plates manufactured by JURID (Part Number (P/N) 100 7A0000-03, P/N 1007A0000-04, or P/N 1007A0000-05) are more sensiti ve to wear than those manufactured by MIBA (P/N 1007A0000-06 or P/N 1007B 0000-01).
For the reason described above, this AD retains the requirements of EASA AD 2010-0267, which is superseded, and requires:

• a repetitive Operational Test of the WTB/POB perfo rmance on the flap and slat systems, and

• embodiment of the terminating action which consists in the installation of WTB standard build on brake plates manufactured by MIBA

.
Effective Date: 29 May 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 30 days after the effective date of this AD, identify the 4 WTB P/Ns of the flap and slat systems installed on an aeropl ane in accordance with the instructions of Airbus Alert Operators Transmis sion (AOT) A27L001-12. (2) A review of Airbus aeroplane inspection report (AIR) or aeroplane maintenance records is acceptable in lieu of the id entification required by paragraph (1) of this AD if the P/N of the installe d WTB can be conclusively identified from that review. (3) If a P/N identified as required by paragraph (1 ) or (2) of this AD is P/N 1007A0000-03, or P/N 1007A0000-04, or P/N 1007A0000 -05, within the compliance time defined in table 1 of this AD and t hereafter at intervals not to exceed 1000 Flight Hours (FH), perform the Opera tional Test of the WTB/POB on the affected flap and/or slat systems in accordance with the instructions of Airbus AOT A27L001-12.

Table 1 – Initial operational test

Compliance time (whichever occurs later, A or B)

A Within 1 000 FH since the last accomplishment of A3 30/A340 Maintenance Review Board Report (MRBR) tasks 27.50. 00/14 and 27.80.00/10 or since aeroplane first flight, as applicable

B Within 30 days after the effective date of this AD

(4) If any operational test as required by paragrap h (3) of this AD fails, before next flight, replace the affected WTB with a servic eable part, in accordance with the instructions of Airbus AOT A27L001-12. (5) Within 90 days after the accomplishment of the identification as required by paragraph (1) or (2) of this AD, report the iden tification results to Airbus. Within 90 days after the accomplishment of each op erational test as required by paragraph (3) of this AD, report any fi nding to Airbus. Both actions are to be accomplished In accordance with the instructions of Airbus AOT A27L001-12. (6) Installation of a WTB having P/N 1007A0000-03, P/N 1007A0000-04 or P/N 1007A0000-05 as replacement part, as required b y paragraph (4) ofEASA AD No.: 2012-0082

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. this AD, does not constitute terminating action for the repetitive tests required by paragraph (3) of this AD. (7) Within 26 months after the effective date of th is AD, replace each WTB having P/N 1007A0000-03, P/N 1007A0000-04 or P/N 10 07A0000-05 with a WTB having P/N 1007A0000-06 in accordance with th e instructions of Airbus AOT A27L001-12. (8) Modification of an aeroplane as required by par agraph (7) of this AD constitutes terminating action for the repetitive t ests required by paragraph (3) of this AD for that aeroplane. (9) As an alternative to the modification required by paragraph (7) of this AD, installation of WTB having P/N 1007B0000-01 in acco rdance with the instructions of Airbus AOT A27L001-12 is acceptable to comply with requirements of paragraph (7) of this AD and consti tutes terminating action for the repetitive tests required by paragraph (3) of this AD. (10) From the effective date of this AD, for aeropl anes on which Airbus Mod. 43512 has been embodied in production, do not insta ll on that aeroplane any WTB having P/N 1007A0000-03, P/N 1007A0000-04 o r P/N 1007A0000-05. From the effective date of this AD, for aeroplanes on which Airbus Mod. 43512 has not been embodied in production, installation of a rep lacement WTB having P/N 1007A0000-03, P/N 1007A0000-04 or P/ N 1007A0000- 05 is allowed provided that, after its installation , it has successfully passed the operational test in accordance with the instruc tions of Airbus AOT A27L001-12.

Ref. Publications: Airbus AOT A27L001-12 dated 26 A pril 2012. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@e asa.europa.eu. 4. For any questions concerning the technical conte nt of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EIAL, Fax: +33 5 61 93 45 80 or + 33 5 61 93 44 51.E-mail: airworthiness. A330-A340@airbus.co m