## EASA EASAAD No:2010-0070 

## AIRWORTHINESS DIRECTIVE AD No.: 2010-0070

Date: 

### 14April 2010 Note: This Airworthiness Directive (AD) 1s issued by EASA, acting in accordance with Regulation (EG) No21612008onbehalfolthe European Community, itsMemberStates andof the European third countries that partlcipdle in the activWesof EASA underArtide 66 of that Regulation. This AD is issued in accordance with EC 1702l2b03, Part 21A.3B. In accordance with EG 204212003Annex 1,Part M.A.301, the continuing airworthiness ofan aircr.Jftshali OsenSuredbyaccomplishing any applicable ADs. Gonsequenliy, no person mayoperate anaircraft 10which anAD applies, except inaccotdance with the requirements ofthatAD unless otherwise spBcffied bytheAgency lEG204212003Annex I,Part M,A.303] oragreed ~ith theAlJthorilyoftheStateof Registry[EG21612008, Article 14(4)exemption]. 

### I Type Approval Holder's Name[l Type/Model designation(s) : AIRBUS A310andA300-600(ST)aeroplanes reDS Number: Foreign AD: Supersedure:



### ATA25
Manufacturer(s):

App[icability:

Reason:

EASA Form 110 France N" 145 and EASAA.014 Not applicab[e This AD supersedes EASA AD 2009-0084 dated 09 April 2009. 

### Equipment / Furnishings - Pilot and Co-pilot Seats - Deactivation of Powered Movement - Modification

Airbus (forrerly Airbus Industrie)

- A310-203, A310-203C, A310-204, A310-221, A310·222, A310-304, A310-308, A310-322, A310-324 and A310-325 aeroplanes, and



### I

~A300B4~p01, A300B4-603, A300B4~605R, A300B4-620, A300B4-622, A300B4-p22R, A300C4-605R Variant F, A300C4-620, A300F4-605R and A300F4-622R aeroplanes, and



### I

- A300F4-p08ST aeroplanes, all manufacturer serial numbers, ifequipped with SOGERMA pilot e[ectriC<lI seat Part Number (PIN) 2510112 series -or co-pilot electriC<lIseats PIN 2510113 series. Prompted by a reported in-service event, EASA issued AD 2009-0084 to prevent unwanted movement of pilot- or co-pilot seat in the horizontal direction which isconsidered as potentially unsafe, especially during the takeoff phase when the speed ofthe aeroplane isgreater than 100 knots and until landing gear retraction. AD 2009-0084 required the deactivation ofthe e[ectriC<l]power of SOGERMA pilot seats PIN 2510112 series and co-pilot seats PIN 2510113 series. Optional intermediate actions were also provided by AD 2009-0084 to allow partial orfull restoration of seat adjustment functionality. Since AD 2009-0084 was issued, apermanent solution has been deve]ope~ that terminates the de-activation requirement and invalidates the intermediate actions. Page 1/3EASAADNo :2010~0070 Consequently, this AD relains requirements of EASA AD 2009-0084, which is superseded, and requires implementing the terminating action. In addition, this AD prohibits the (re)installation of unmodified pilol- and co-pilot seats on any aeroplane that has been modified in accordance with the requirements of this AD. Effective Date: 28 April 2010 Required as indicated, unless already accomplished: (1) Within the nexl15 days after 23April 2009 [the effective date of EASA AD 2009-0084], de-activate the electrical supply of SOGERMA PIN 25101 112 series pilot seats andfor SOGERMA PIN 2510113 series copilot syats, in accordance with the instructions ofAirbus All Operators Telex ~AOT) A310-25A2203 Revision 02 orAOT A300-25A6215 Revision (2) 02 ortOT A300-25A9010 Revision 02, as applicable to aeroplane model. Optioral intermediate actions: (2.1) restoration ofvertical seat electrical adjustment: lfleactivation of electrical powered horizontal movement of SOGERMA 2510112 series pilot seats andlor SOGERMA 2510113 series co-pilot seals in accordance with the instructions of SOGERMA Alert Service Bulletin A2510112-25-764 original issue, allows restoration ofthe vertical adjustment only. (2.2) Restoration ofvertical and horizontal seat electrical adjustment: Repetitive inspections ofthe switch position 'S4' and the related shim of SOGERMA 2510112 series pilot seats and/or SOGERMA 2510113 series co-pilot seats at intervals nol to exceed 2 months in accordance with SOGERMA Inspection Service Bulletin 2510112- Required Action{s) 25-807 original issue, allows reactivation of both horizontal and and Compliance vertical electrical movements, provided the measurement results of Time{s): each inspection are within the acceptable value indicated in the SOGERMA Inspection Service Bulletin 2510112-25-807 original issue. Within 30 days after the first inspection, send adetailed and tomplete fleet inspection report, including measurement value(s) Fnd PIN and serial number for each seat, to Airbus. (3) Terminating Action Withih the next 12 months after the effective date ofthis AD, modify the aeroplane by installing an enlarged shim for horizontal switch actuation on e~ch affected seat in accordance with the instructions ofAirbus SB A310L25-2205. or A300-25-6217, orA300-25-9011, as applicable 10 aeroplane model. After modification of an aeroplane as required by this paragraph, the requirements of paragraph (1) of this AD no longer apply and the optional intermediate actions of paragraph (2) are no longer acceptable. (4) After modification of an aeroplane as required by paragraph (3) ofthis AD, do not install any SOGERMA pilot electrical seat PIN 2510112 series or co-pilot electrical seat PIN 2510113 series on that aeroplane, unless the seat has been modified in accordance with the instructions ofAirbus S8 A310-25-2205. orA30G-25-6217, orA300-25·9011. as applicable to aeroplane model. AIRBUS AOT A310-25A2203 Revision 02, AOT A300-25A6215 Revision 02 and AOT A300-25A9010 Revision 02. Ref. Publications: AIRBUS ,service Bulletin A310-25·2205 Original issue, A300-25-6217 Original issue, A3PO-25-9011 Original issue.

, SOGERMA Alert Service Bulletin A2510112-25-764 orioina! issue. EASAForm110 Page 213EASA AD No: 2010-0070 SOGERMA Inspection Service Bulletin 

### 2510112-25-807 original issue. The use of later approved revisions ofthese documents is acceptable for compliance with the requirements ofthis AD. 

### 1. Ifrequested and appropriately substantialed, EASA can approve Alternative Methods of Compliance for this AD. 

### 2. This AD was posted on 

### 25January 

### 2010as PAD 

### 10-014for consultation until 

### 22 February 

### 2010. No comments were received during the consultation period. Remarks: 

### 3 Enquiries regarding this AD should be referred 10the Airworthiness Directives, Safety Management & Research Section, Certification Directorate, EASA. E-mail ADs@eas8.europa.eu. 4. For any question concerning the technical content ofthe requirements in this AIf, please contact: AIRBUS SAS - EAW (Airworthiness Office, Telephone: 

### +33 561933696, Fax: +

### 33561934451). I

EASA Form 110 Page3/3