## EASA EASAAD No.:2006-0111R1 

## AIRWORTHINESS DIRECTIVE AD No.: 2006-0111 R1

Date:26August 2009
Note: ThisAirworthiness Directive (AD) isissued byEASA, acting inaCOJrdancewith Regulation (EC) No21612008OIlbehalfofthe European Community. its Member States andof the European third countries thaI participate intheactivities of EASAunderArticle 66ofthatRegulatiollThis AD is issued in accordance with EC 170212003,Part 21A_3B. Inaccordance with EC 2042/2003 Annex I. Part MA301, the continuing airworthiness ofan aircraft shall beensured byaccomplishing anyapplicable ADs_COl1sequently,no person mayaperale an aircraft towh;ch an AD applies, excepl inaccordance wilh the requirements ofthatAD, unless otherwise specified bythe Agency IEC204212003Annex I,Pari MA303] oragreed wilh IheAulhority ofthesjate of Reg;stry[EG216/2008. Article 14(4)exemption]_ 

### TypeApproval 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 

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

### I Flight Controls - FlapsTransmission Shaft- Inspection IRepair

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 aswiper 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 10correcl the compliance time of 400 flight cycles in paragraph (3) into 400 flight hours. In addition, paragraph (4) has been jntroduced 10clarify 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_

Page 1/2EASAAD 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 ofthis 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. 

### I (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. I , 1. Ifrequested 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 5619344 51).

EASA Form 110 Page 212