EASA AD No.: 2014-0011R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0011R1

Date: 17 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 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign 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 aeroplanes, all manufacturer serial numbers.

Reason: In the frame of the A320 Extended Service Goal (ESG) project and the study 

on the Trimmable Horizontal Stabilizer Actuator (THSA), a sampling 

programme of in-service units has been performed and several cases of wear

at different THSA levels were reported.

This condition, if not detected and corrected, would reduce 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 reasons described above, this AD requires repetitive inspections 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 2014
EASA AD No.: 2014-0011R1

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time defined in Table 1 of this AD, and, thereafter, 

at intervals as defined in Table 2 of this AD, as applicable, accomplish a 

special detailed inspection (SDI) of the THSA in accordance with the 

instructions of Airbus SB A320-27-1227 Revision 01.

Table 1: THSA Initial SDI

Compliance time (whichever occurs later, A or B)

A Before the THSA accumulates 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: Repetitive SDI Intervals

FH accumulated 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 

addition, after initiating the 4-month interval, the THSA replacement 

requirement of paragraph (3) must be taken into account.

(2) If, during any SDI 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 Table 3 of this AD, as applicable, 

replace each THSA with a serviceable THSA in accordance with the 

instructions of Airbus SB A320-27-1227 Revision 01.

Table 3: THSA Replacement

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) Replacement of a THSA on an aeroplane as required by paragraph (2) or

(3) of this 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 on the FH or FC accumulated by the 

replacement THSA, refer to Table 1 or Table 2 of this AD, as applicable,

to determine the next due SDI.

(5) An 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.
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(6) A THSA that has 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 on the FH or FC 

accumulated by the repaired THSA, refer to Table 1 or Table 2 of this AD, 

as applicable, to determine the next due SDI.

(7) From the effective date of this AD, installation 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. Publications: Airbus SB A320-27-1227 original issue dated 01 July 2013, or Revision 01

dated 07 October 2013.

UTAS CMM 27-44-51.

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. The original issue of this 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.