E ASA AD No.: 20 13
- 0 251

TE.CAP.00110
- 003 © European Aviation Safety Agency. All rights reserved
. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 13 - 0 251 [Correction: 16 October 2013]
Date: 15 October 2013
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 ope rate an aircraft to which an AD applies, except in accorda nce 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) exempt ion]

. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A330 and A340 aeroplanes
TCDS Number: EASA.A.004 and EASA.A.015 F oreign AD: Not applicable Supersedure: None



### ATA 27 Flight Controls – Spoiler Servo C ontrol / Hydraulic Locking

Function – Operational Test
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 M anufacturer S erial N umber s (MSN). Airbus A340
- 211 , A340
- 212 , A340
- 213 , A340
- 311 , A340
- 312 , A340
- 313 , A340
- 541 , A340
- 542 , A340
- 643 and A340
- 642 aeroplanes, all MSN. Reason: During post
- flight maintenance check s accomplished on an A330 and on an A340 aeroplane , it was identified that seven spoiler servo
- controls MZ series had lost their hydraulic locking function. The results of the subsequent technical investigation accomplished in
- shop by the part supplier confirmed the system failure was due to a sheared seal on the blocking valve , ensuring the blocking function of the spoiler. It is suspected that the seal damage may have occurred during accomplishment of a modification to fit a new design of maintenance cover on wing, required by EASA AD 2008
- 0160. This condition , if not detected and corrected, in combination with one engine inoperative at take
- off , could result in reduce d control of the aeroplane

. Prompted by these findings , Airbus issued A l l Operators T elex (AOT) A330
- 27A3185 and AOT A340
- 27A4181 to request a one
- time operational test of the Hydraulic Locking Function for aeroplane s on which MZ type Spoiler Servo Control (SSC) Part Number (P/N) MZ4339390
- 12 or P/N MZ4306000
- 12 are fitted, and EASA issued AD 2012
- 0009 to require accomplishment of this test

.E ASA AD No.: 20 13
- 0 251

TE.CAP.00110
- 003 © European Aviation Safety Agency. All rights reserved
. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. Since that AD was issued , Airbus re
- assessed the situation and determined that it is necessary to introduce repetitive inspections of the SSC, irrespective of SSC type

. Airbus issued three SB s for those repetitive inspe ction s on all A330, A340, and A340
- 500/600 aeroplanes

. For the reason describe above, this AD require s repetitive operational test s of the hydraulic locking function of the SSC installed on the Blue and Yellow hydraulic circuits , irrespective of SSC type, and, depending on test results, replacement of the SSC

. This AD has been re
- published to correct the date (month) of publication. Effective Date: 29 October 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Initially, w ithin the compliance time define d in the Table 1 of this AD , and , thereafter , at interval s not to exceed 48 months, accomplish a n operational test of the hydraulic locking function on each SSC (any type), when fitted on Bl u e or Yellow hydraulic circuits, in accordance with the instructions of Airbus SB A330
- 27
- 3195, or SB A340
- 27
- 4188 , or SB A3 4 0
- 27
- 5059 , as applicable

. Table 1 Initial Operational Test T hreshold

Compliance time, whichever occurs later , A or B
A Within 48 m onths since aeroplane first fligh t , or since accomplishment of an operational test in accordance with the instructions of Airbus AOT A330
- 27A3185 or AOT A340
- 27A4181 , as applicable B Within 24 months after the effective date of this AD (2) If , during any operational test as required by paragraph (1) of this AD, the hydraulic locking function of a SSC fails the test , before next flight, replace the affected SSC with a serviceable part , in accordance with the instruction s of Airbus SB A330
- 27
- 3195, or SB A340
- 27
- 4188, or SB A340
- 27
- 5059, as applicable

. (3) Replacement of a SSC does not constitute terminating action for the repetitive operational test s as required by paragraph (1) of this AD. Ref. Public ations: Airbus AOT A330
- 27A3185 , dated 04 January 2012

. Airbus AOT A340
- 27A4181 , dated 04 January 2012

. Airbus SB A330
- 27
- 3195, o riginal issue dated 07 December 2012

. Airbus SB A340
- 27
- 4188, o riginal issue dated 07 December 2012

. Airbus SB A340
- 27
- 5059, o riginal issue dated 10 April 2013

. 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 29 August 2013 as PAD 13
- 13 1 for consultation until 26 September 2013. 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

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

.