EASA

EASA AD No : 2010-0070

AIRWORTHINESS DIRECTIVE

AD No.: 2010-0070

Date: 14 April 2010

Note: This Airworthiness Directive (AD) 1s issued by EASA, acting in accordance with

Regulation (EG) No 21612008 on behalfolthe European Community, its Member States and of

the European third countries that partlcipdle in the activWes of EASA under Artide 66 of that

Regulation.

This AD is issued in accordance with EC 1702l2b03, Part 21A.3B. In accordance with EG 204212003 Annex 1, Part M.A.301, the

continuing airworthiness of an aircr.Jft shali Os enSured by accomplishing any applicable ADs. Gonsequenliy, no person may operate

an aircraft 10which an AD applies, except in accotdance with the requirements of that AD unless otherwise spBcffied by the Agency

lEG 204212003Annex I, Part M,A.303] or agreed ~ith the AlJthorily of the State of Registry [EG 21612008, Article 14(4) exemption]. I

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

AIRBUS A310 and A300-600(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, if equipped with SOGERMA pilot e[ectriC<lI

seat Part Number (PIN) 2510112 series - or co-pilot electriC<lI seats 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 is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until

landing gear retraction.

AD 2009-0084 required the deactivation of the 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 or full restoration of seat adjustment functionality.

Since AD 2009-0084 was issued, a permanent solution has been deve]ope~

that terminates the de-activation requirement and invalidates the intermediate

actions.

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EASA AD No : 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 23 April 2009 [the effective date of EASA

AD 2009-0084], de-activate the electrical supply of SOGERMA PIN

25101

1

12 series pilot seats andfor SOGERMA PIN 2510113 series copilot syats, in accordance with the instructions of Airbus All Operators

Telex ~AOT) A310-25A2203 Revision 02 or AOT A300-25A6215 Revision

(2)

02 or tOT A300-25A9010 Revision 02, as applicable to aeroplane model.

Optioral intermediate actions:

(2.1) restoration of vertical 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 of the vertical adjustment only.

(2.2) Restoration of vertical and horizontal seat electrical adjustment:

Repetitive inspections of the 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 a detailed 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 of this AD, modify the

aeroplane by installing an enlarged shim for horizontal switch actuation

on e~ch affected seat in accordance with the instructions of Airbus SB

A310L25-2205. or A300-25-6217, or A300-25-9011, 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) of this

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 of Airbus

S8 A310-25-2205. or A30G-25-6217, or A300-25·9011. 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 213
EASA AD No: 2010-0070

SOGERMA Inspection Service Bulletin 2510112-25-807 original issue.

The use of later approved revisions of these documents is acceptable for

compliance with the requirements of this AD.

1. If requested and appropriately substantialed, EASA can approve

Alternative Methods of Compliance for this AD.

2. This AD was posted on 25 January 2010 as PAD 10-014 for consultation

until 22 February 2010. No comments were received during the

consultation period.

Remarks: 3 Enquiries regarding this AD should be referred 10 the Airworthiness

Directives, Safety Management & Research Section, Certification

Directorate, EASA. E-mail ADs@eas8.europa.eu.

4. For any question concerning the technical content of the requirements in

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

Telephone: + 33 5 61933696, Fax: + 33 5 61934451).

I

EASA Form 110 Page 3/3