EASA AD No. : 2010-0193 

EASA Form 110 Page 1/4 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0193 

Corrected: 11 October 2010 

Date: 29 September 2010 

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 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 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]. 

Type Approval Holder’s Name : 

AIRBUS 

Type/Model designation(s) : 

A340-200/-300 aeroplanes 

TCDS Number : EASA.A.015 

Foreign AD : Not applicable 

Supersedure : This AD supersedes DGAC France AD F-2002-415R2 dated 30 October 2002.

ATA 27 Flight controls – Trimmable Horizontal Stabilizer Actuator 

Screw/Nut Assembly - Inspection / Lubrication

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A340 aeroplanes, models -211, -212, -213, -311, -312 and -313, all 

manufacturer serial numbers. 

Reason: Several cases of transfer tube disconnection from the ball-nut of the 

trimmable horizontal stabilizer actuator (THSA) part number (P/N) 47172 

and 47147-400 were detected on the ground during greasing and 

maintenance. 

This condition is caused by water ingress into the ball-nut resulting in the 

jamming of the ball transfer circuit when the water freezes. 

If the three (independent) ball circuits fail, then the THSA will operate on a 

fail-safe nut. This nut (which operates without balls) would then jam after 

several movements on the screw of the THSA. 

This degraded operation is not detectable in the cockpit by the crew as 

long as the THSA does not jam and could damage the ball screw and the 

fail-safe nut. 

To detect this unsafe condition, DGAC France AD F-2001-357 was issued 

to require repetitive inspections of the transfer tubes and their collars in 

order to detect at an early stage any distortion or initiation of 

disconnection. 

Further to a new case of transfer tube disconnection, DGAC France AD 

F-2001-357R2 required an additional repetitive greasing task with 
EASA AD No. : 2010-0193 

EASA Form 110 Page 2/4 

 

reinforcement of the ball-nut maintenance greasing instructions. 

In addition, the electrical flight control computers monitor the operation of 

the THSA and the jamming of this actuator could be detected and 

indicated by messages on the maintenance system and on the ECAM. In 

this case a mandatory inspection of the THSA is required before the next 

flight. 

DGAC France AD F-2002-037 required application of a final fix [related to 

inspection and greasing task required by DGAC France AD F-2001-357] 

for the THSA PN 47172 by accomplishment of Airbus modification 

49590/Service Bulletin (SB) A340-27-4089 changing the THSA P/N from 

47172 to 47172-300. 

Later on, DGAC France AD F-2002-415R2 superseded DGAC France AD 

F-2001-357R2 and F-2002-037, requiring: 

- the repetitive inspection of all THSA P/N in service, and 

- the lubrication of some THSA P/N, and 

- the replacement of THSA P/N 47172, 47147-400 and 47147-2XX/-3XX 

Airbus has later introduced 4 new THSA P/N (47172-500, 47172-510, 

47172-520 and 47172-530). 

This AD retains the requirement of DGAC AD F-2002-415R2, which is 

superseded, and requires repetitive inspections and lubrications of the 

new THSA P/N. 

The repetitive inspection and lubrication requirements for THSA P/N 

47172-520 and 47172-530 shall also be included in the next Airworthiness 

Limitation Section (ALS) Part 4 revision. 

This AD correction is issued to clarify the requirements of paragraphs (4) 

and (6) in the Required actions and Compliance Times section. 

Effective Date: 13 October 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, after the effective date of this AD: 

(1) Restatement of DGAC AD F-2002-415 R2:

(1.1) Modification of THSA PN 47172:

Before 31 December 2003, [effective date of DGAC AD F-2002-415 

R2] modify the ball-nuts of THSA P/N 47172 in accordance with the 

instructions of Airbus Service Bulletin (SB) A340-27-4089. The THSA 

P/N 47172 becomes P/N 47172-300 after accomplishment of the 

modification. 

(1.2) Modification of THSA’s PN 47147-400 and 47147-2XX/3XX:

Before 31 July 2004, [effective date of DGAC AD F-2002-415 R2] 

- modify the ball-nuts of THSA P/N 47147-400 in accordance with the 

instructions of Airbus Airbus SB A340-27-4099. The THSA P/N 

47147-400 becomes P/N 47147-500 after accomplishment of the 

modification. 

- modify THSA’s P/N 47147-200, -210, -213, -300, -303 and -350 in 

accordance with the instructions given in Airbus SB 

A340-27-4099 and Airbus SB A340-27-4059. The THSA P/N 

47147-2XX/3XX become P/N 47147-500 after accomplishment of 

the modification. 
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(2) Ball screw assembly inspection: 

For all aeroplanes except those on which Airbus Modifications 52269 

and 56056 and 55780 have been embodied in production, and except 

those on which Airbus SB A340-27-4136 at original issue up to 

Revision 02 and Airbus SB A340-92-4056 Revision 03 have been 

embodied in service: 

(2.1) For aeroplanes on which Airbus SB A340-27-4136 at original issue 

up to Revision 02 has been embodied in service: 

Before the accumulation of 700 flight hours (FH) after the effective 

date of this AD and, thereafter, at intervals not exceeding 700 FH 

from the last inspection, perform a detailed inspection of the ball 

screw assembly for integrity of the primary and secondary load path 

and check the Checkable Shear Pins (CSP), and do the applicable 

corrective actions, in accordance with the accomplishment 

instructions of Airbus SB A340-27-4107 Revision 8. 

(2.2) For aeroplanes on which Airbus SB A340-27-4136 has not been 

embodied in service: 

Before the accumulation of 700 FH after the effective date of this AD 

and, thereafter, at intervals not exceeding 700 FH from the last 

inspection, perform a detailed inspection of the ball screw assembly 

for integrity of the primary and secondary load path, and do the 

applicable corrective actions, in accordance with the accomplishment 

instructions of Airbus SB A340-27-4107 Revision 8. 

(2.3) If one of the "PRIM X PITCH FAULT" or "STAB CTL FAULT" 

messages is displayed on the ECAM associated with the "PITCH 

TRIM ACTR (1CS)" maintenance message, inspect the THSA 

before the next flight following the messages display, in accordance 

with the instructions of paragraph (2.1) or (2.2) of this AD, as 

applicable to the aeroplane configuration, and do the applicable 

corrective actions. 

(3) Ball screw nut lubrication of all THSA: 

Unless already accomplished, for all aeroplanes, before the 

accumulation of 700 FH after the effective date of this AD and, 

thereafter, at intervals not exceeding 700 FH from the last lubrication 

of the THS actuator ball screw nut, 

perform A340 MRBR Revision 12 task 27.40.00/02 (Lubrication of 

THS actuator ball screw nut). 

(4) For aeroplanes fitted with THSA P/N 47147-500, 47147-700, 

47172-300, 47172-500 or 47172-510, accomplishment of the 

repetitive requirements of A340 ALS Part 4 tasks 274400-00001-1-E, 

274400-00001-2-E, 274400-00001-3-E or 274400-00001-4-E, as 

applicable to the aeroplane configuration, is acceptable to comply with 

the requirements of paragraphs (2.1) and (2.2) of this AD. 

(5) For aeroplanes fitted with THSA P/N 47147-500, 47147-700, 47172-

300, 47172-500 or 47172-510, accomplishment of the repetitive 

requirements of A340 ALS Part 4 tasks 274400-00002-1-E, is 

acceptable to comply with the requirements of paragraph (3) of this 

AD. 

(6) Before the effective date of this AD, accomplishment of the 

instructions of Airbus SB A340-27-4107 Revision 02 up to Revision 

07, is acceptable to comply with the requirements of paragraph (2.1) 
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and (2.2) of this AD. After the effective date of this AD, the repetitive 

inspection requirements of paragraph (2) of this AD must be complied 

with. 

(7) Before the effective date of this AD, accomplishment of the 

instructions of Airbus A340 MRBR Revision 12 task 27.40.00/02 up to 

Revision 11, is acceptable to comply with the requirements of 

paragraph (3) of this AD. After the effective date of this AD, the 

repetitive inspection requirements of paragraph (3) of this AD must be 

complied with. 

Ref. Publications: Airbus SB A340-27-4107 Revision 08; 

Airbus A340 ALS Part 4 Revision 01; 

Airbus A340 MRBR Revision 12; 

Airbus SB A340-27-4136 at original issue; 

Airbus SB A340-92-4056 Revision 03. 

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 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 to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail: ADs@easa.europa.eu 

4. For any questions concerning the technical content of the 

requirements in this AD, please contact: AIRBUS – Airworthiness 

Office – EAL; E-mail: airworthiness.A330-A340@airbus.com .