EASA AD No.: 2014

- 001 1 R1

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2014 - 001 1 R1

Date: 1 7 January 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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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 ): A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable

Revision : This AD revises EASA AD 2014

- 0011 dated 09 January 2014.



### ATA 27 Flight Controls

– Trimmable Horizontal Stabilizer Actuator

–

Inspection

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 aeroplane s , all manufacturer seria l numbers

. Reason: In the frame of the A320 Extended Service G oal (ESG) project and the study on the Trimmable Horizontal Stabilizer Actuator (THSA) , a sampling program me of in

- service units has been performed and several cases of wear at different THSA levels were reporte d. This condition , if not detected and corrected , w ould reduc e the remaining life of the THSA , possibly resulting in premature failure and consequent reduced control of the aeroplane

. Prompted by these findings, Airbus issued Service Bulletin (SB) A320

- 27

- 1227 to provide THSA inspection instructions. For the reason s describe d above, this AD requires r ep etitive inspection s of the THSA and introduces a life limit for the THSA. This AD has been revised to correct and clarify paragraph (2).
Effective Date: Revision 1 (same as original issue): 23 January 2014EASA AD No.: 2014

- 001 1 R1

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 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 the compliance time define d in T able 1 of this AD , and , thereafter, at interval s as defined in Table 2 of this AD , as applicable, accomplish a special detail ed inspection ( SD I ) of the THSA in accordance with the instructions of Airbus SB A320

- 27

- 1227 R evision 0 1

.

Table 1 : THSA I nitial SDI Compliance time (whichever occurs later, A or B) A Before the THSA accumulate s 48 000 flight hours ( FH ) or 30 000 flight cycles ( FC ) , whichever occurs first since first installation on an aeroplane B Within 4 months after the effective date of this AD

Table 2 : Repeti ti ve SDI I ntervals FH ac cumulated by the THSA ( on the effective date of this AD, since first installation on an aeroplane ) Repeat interval (see Note 1)
Less than 67 500 FH 24 months 67 500 FH or more 4 months
Note 1: From the intervals defined in Table 2 of this AD, it should be clear that, after exceeding 67 500 FH, the 4

- month interval applies to the THSA . In a ddition, after initiating the 4

- month interval, the THSA replacement requirement of paragraph (3) must be taken into account. (2) If, during any SD I as required by paragraph (1) of this AD, any discrepancy is found, replace the THSA with a serviceable THSA within the applicable compliance time, depending on findings and/or oil sample spectrometric test results, as specified in, and in accordance with the instructions of, Airbus SB A320

- 27

- 1227 Revision 01

. Note 2: For the purpose of this AD, a serviceable THSA is a THSA that has accumulated less than 67 500 FH since first installation on an aeroplane. ( 3 ) Within the compliance time defined in T able 3 of this AD , as applicable, replace each THSA with a serviceable THSA in accordance with the instructions of Airbus SB A320

- 27

- 1227 R evision 01.

Table 3: THSA R eplacement Compliance time (whichever occurs later , C or D ) C Before exceeding 67 500 FH since first installation on an aeroplane D Within 12 months after the effective date of this AD ( 4 ) R e placement of a THSA on an aeroplane as required by paragraph (2) or (3) of t h is AD , as applicable, does not constitute terminating action for the repetitive SDI required by paragraph (1) of this AD for that aeroplane

. Following replacement , depending o n the FH or FC accumulated by the replacement THSA , r efer to T able 1 or Table 2 of this AD, as applicable , to determine the next due SDI

. ( 5 ) A n inspection, accomplished before the effective date of this AD in accordance with the instructions of Airbus SB A320

- 27

- 1227 at original issue dated 01 July 2013 , is acceptable to comply with the initial inspection as required by paragraph (1) of this AD.EASA AD No.: 2014

- 001 1 R1

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. ( 6 ) A THSA that ha s been repaired in shop, in accordance with United Technologies Corporation Aerospace Systems ( UTAS ) Component Maintenance Manual ( CMM ) 27

- 44

- 51 ( at any revision ) , is considered equivalent to having passed an inspection in accordance with the instructions of Airbus SB A320

- 27

- 1227. Depending o n the FH or FC accumulated by the rep a ired THSA , r efer to T able 1 or Table 2 of this AD, as applicable , to determine the next due SDI

. ( 7 ) From the effective date of this AD, i nstallation on an aeroplane of a THSA having accumulated or exceeded 67 500 FH is allowed, provided that, prior to installation, the THSA has been modified /inspected in accordance with Airbus approved aeroplane modification instructions. Contact Airbus to obtain the necessary approved modification instructions.
Ref. Public ations: Airbus SB A320

- 27

- 1227 original issue dated 01 July 2013, or R evision 0 1 dated 07 October 2013

. UTAS CMM 27

- 44

- 51

. The u se of later approved revisions of th e s e document s 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. Th e original issue of th is AD was posted on 13 November 2013 as PAD 13

- 166 for consultation until 11 December 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

.