EASA

EASA AD No.: 2006-0111R1

AIRWORTHINESS DIRECTIVE

AD No.: 2006-0111 R1

Date: 26 August 2009

Note: This Airworthiness Directive (AD) is issued by EASA, acting in aCOJrdancewith

Regulation (EC) No 21612008 OIl behalf of the European Community. its Member States and of

the European third countries thaI participate in the activities of EASA under Article 66 of that

RegulatiollThis AD is issued in accordance with EC 170212003, Part 21A_3B. In accordance with EC 2042/2003 Annex I. Part MA301, the

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs_ COl1sequently, no person may aperale

an aircraft to wh;ch an AD applies, excepl in accordance wilh the requirements of that AD, unless otherwise specified by the Agency

IEC 204212003 Annex I, Pari MA303] or agreed wilh Ihe Aulhority of the sjate of Reg;stry [EG 216/2008. Article 14(4) exemption]_

Type Approval Holder's Name: TyJe/Model designation(s) :

AIRBUS SAS

TeDS Number:

Foreign AD:

Revision:

ATA27

Manufacturer(s):

Applicability:

Reason:

EASA Form 110

A310 aeroplanes

France No. 145

Not app[icable

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This AD revises and replaces EASA tD 2006-0111 dated 12 May 2006.

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Flight Controls - Flaps Transmission Shaft - Inspection I Repair

Airbus (formerly Airbus Industrie)

Airbus A310 aeroplanes, all certified models, a[1serial numbers.

During High Time Equipment (HirE) reviews conducted within the scope of the

A310 aircraft Design Service Goal (DSG) extension work, Airbus discovered

that the splined couplings and the sliding bearings of the flap transmjssion

system could be affected by corrosion and wear, especially when their

protective components such as wiper rings and rubber gaiters could become

defective.

This condition, if not detected and corrected, could degrade the functional

integrity of the flap transmission system.

For the reason described above~ this AD requires repetitive inspections of the

flap transmission system and associaled components, and corrective

action(s), depending on findings!

This AD has been revised 10 correcl the compliance time of 400 flight cycles in

paragraph (3) into 400 flight hours. In addition, paragraph (4) has been

jntroduced 10 clarify that the correctjve actions do not end the requirement to

continue the repetitive inspections, and some editorial changes for reasons of

standardization. These do not affect the requirements of this AD as originally

intended_

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EASA AD No.: 2006-0111R1

Effective Date: 19 May 2006

Required as indicated, unless accomplished previously:

(1 ) Within the next 2 500 flight cycles (FC) after the effective date of this AD,

inspect the splined couplings and the sliding bearings of the flap

transmission shaft, in accordance with the instructions of Airbus Service

Bulletin (SB) A310-27-2099.

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(2) Thereafter, at intervals not ,10exceed 2 500 FC, repeat the inspection of

Required Action(s) the splined couplings and tre sliding bearings of the flap transmission

and Compliance shaft, in accordance with t1e instructions of Airbus S8 A310-27-2099.

Time{s): (3) If, during any inspection as required by paragraph (1) or (2) of this AD, a

defect is observed, within 400 flight hours after the discovery, remove the

affected component and accomplish the corrective actions in accordance

with the instructions of Airbus SB A310-27-2099.

(4) Accomplishment of corrective actions as required by paragraph (3) of

this AD does not constitute teminating action for the repetitive

inspections as required by paragraph (2) of this AD.

AIRBUS Service Bulletin A310-27-2099 original issue or Revision 01.

Ref. Pubiications: The use of later approved revisiqns of this document is acceptable for

compliance with the requirements of this AD.

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,

1. If requested and appropriate,ly substantiated, EASA can approve

Alternative Methods of Compliance for this AD.

2. The Original issue of this AD was posted on 15 February 2006 as PAD 06-

034 for consultation until 14 March 2006. No comments were received

during the consultation period.

Remarks: 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 question concerning the technical content of the requirements in

this AD, please contact: AIRBUS SAS - EAW (Airworthiness Office,

Telephone: + 33 5 61 1841 39, Fax: + 33 5 619344 51).

EASA Form 110 Page 212