EASA AD No.: 2015-0081

TE.CAP.00110-004 © European Aviation Safety Agency. All 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.: 2015-0081

Date: 07 May 2015

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 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 otherwi se specified by the Agency [EU 1321/2014 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): A300-600, A300-600ST and A310 aeroplanes

TCDS Numbers: EASA.A.014 and EASA.A.172

Foreign AD: Not applicable

Supersedure: None



### ATA 27 Flight Controls – Trimmable Horizontal Stabilizer A ctuator – Identification / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300 B4-601, A300 B4-603, A30 0 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 C4-605R variant F, A300 C4-620, A300 F4-605R, A300 F4-622R, A300 F4-608ST, A310-203 , A310-203C, A310-204, A310-221, A310-222, A310-304, A310-308, A 310-322, A310-324 and A310-325, aeroplanes, all manufacturer serial n umbers.

Reason: During endurance qualification tests on a T rimmable Horizontal Stabilizer Actuator (THSA) concerning another aeroplane type, a partial loss of the noback brake (NBB) efficiency was experienced. Invest igation results concluded that this partial loss of braking efficiency in som e specific aerodynamic load conditions was due to polishing and auto-contaminat ion of the NBB carbon friction disks. Due to design similarity on the A300-600, A300-600S T and A310 fleet, the same tests were initiated by the THSA manufacturer on certain type THSA, sampled from the field. Subject tests confirmed tha t THSA Part Number (P/N) 47142 series, as installed on the A300-600, A300-60 0ST and A310 fleet, are also affected by this partial loss of NBB efficienc y. This condition, if not detected and corrected, and in conjunction with the power gear not able to keep the ball screw in its last co mmanded position, could potentially lead to an uncommanded movement of the Horizontal Stabilizer, possibly resulting in loss of control of the aeropl ane. For the reasons described above, this AD requires t he removal from service of each affected THSA, with the intent of in-shop NBB carbon disk replacement.

Effective Date: 21 May 2015EASA AD No.: 2015-0081

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Note 1: The THSA affected by the requirements of th is AD are only those identified by P/N 47142-403, 47142-413, 47142-414, or 47142-423. EASA AD 2010-0224 required installation of three secondary retention plates for the gimbal bearings on the THSA upper primary a ttachment, which involved a THSA P/N change from -300 series to -400 series. Note 2: For the purpose of this AD, a serviceable T HSA is a unit (as identified in Note 1 of this AD), which has not exceeded the f light cycle (FC) limits specified in Table 1 of this AD, since first instal lation of the THSA on an aeroplane, or since last NBB disk replacement (see Note 4 of this AD), whichever is later; or a THSA with a different P/N, not affected by the requirements of this AD. Note 3: The life limits as specified in the current revision of ALS Part 4 are still relevant for the affected THSA, as applicable to ae roplane model. This AD addresses a replacement limit for the NBB disks ins talled on the THSA, not the life limit for the THSA itself. (1) Not later than the date specified in Table 1 of this AD, as applicable, determine the FC accumulated by each THSA since fir st installation on an aeroplane, or since last NBB replacement (see Note 4 of this AD), whichever is later, and, for those having reached o r exceeded on that date the corresponding number of FC as specified in Tabl e 1 of this AD, replace the THSA with a serviceable unit (see Note 2 of thi s AD) in accordance with the instructions of Airbus Service Bulletin (S B) A300-27-6070, or Airbus SB A300-27-9022, or Airbus SB A310-27-2106, as applicable. Note 4: In case no maintenance records concerning l ast NBB disk replacement are available, the FC accumulated since first insta llation of the THSA on an aeroplane apply. (2) From each date as specified in Table 1 of this AD, and before exceeding the FC limit corresponding to each date

, as applicable, replace each THSA with a serviceable unit (see Note 2 of this AD) in accordance with the instructions of Airbus SB A300-27-6070, or Airbus S B A300-27-9022, or Airbus SB A310-27-2106, as applicable. Table 1 – THSA Removal for NBB Disks Replacement

Date THSA FC Limit (since first installation on an

aeroplane, or since last NBB replacement,

whichever is later) 01 February 2016 30 000 FC 01 February 2017 20 000 FC 01 February 2019 14 600 FC

Conditions for the installation of a THSA on an aer oplane : (3) From each date specified in Table 1 of this AD, as applicable, it is allowed to install a THSA on an aeroplane, provided the uni t has not exceeded the corresponding number of FC specified in Table 1, si nce first installation on an aeroplane, or since last NBB replacement, whiche ver occurred later.

Ref. Publications: Airbus SB A300-27-6070 original issue, dated 17 February 2015. Airbus SB A300-27-9022 original issue, dated 17 Feb ruary 2015. Airbus SB A310-27-2106 original issue, dated 17 Feb ruary 2015. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.EASA AD No.: 2015-0081

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 30 March 2015 as PAD 15-02 9 for consultation until 27 April 2015. No comments were received duri ng the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS – EIAW (Airworthine ss Office), E-mail: continued.airworthiness-wb.external@airbus.com

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