EASA

EASA AD No_: 2010-0091

AIRWORTHINESS DIRECTIVE

AD No.: 2010·0091

Date: 19 May 2010 J

Note: This Airworthiness Direct; e (AD) is Issued by EASA. acting in accordance with

Regulation (EC) No 21612008 on bkhatf of the European Community, Its Member Slates and of

the European third countries !hOltparticipate 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 204212003 Anne)!. I. Part MA301, the

conlinuing airworthiness ot an aircraft shall he ensured by accomplishing any applicable ADs GonsequenUy. no persoll may operate

an aircraft to which an AD applies. except in acwrdance with the requirements of that AD, unless otherwise specified by the Agency

[EG 204212003 Annex I, Part M.A.303} or agreed with the Authority of the Slate of Registry {EG 21612008, Article 14(4) exemptionl.

Type Approval Holder's Name:

AIRBUS

TCDS Number. EASA.A.064

Foreign AD : Not applicable

Supersedure: None

Type/Model designation(s) :

A318, A319, A320 and A321 aeroplanes

ATA 55 Stabilizers - Elevators -Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Airbus A31B-111, A318-112, A31B-121, A318-122, A319-111, A319-112,

A319-113, A319-114, A319-t 15, A319-131, A319-132, A319-133, A320-111,

Applicability: A320-211, A320-212, A320-21~, A320-215, A320-216, A320-231, A320-232,

A320-233, A321-111, A321-112, A321-131, A321-211 , A321-212, A321-213,

A321-231 and A321-232 aeroplane models, all manufacturer serial numbers.

Reason:

EASA Form 110

A special detailed inspection of A318/ A3191 A320 / A321 elevators premodification 35515 was introduced under AU task 552007 in the ALS part 2

under All Document reference AI/SE·M4/95A.0252196 at issue 7 approved by

EASA on 07 February 2006 and mandated by EASA AD 2006-0165. This All

task has been introduced with an applicability defined at aeroplane

modification level.

A specific statement related to the interchangeable parts policy was introduced

in issue 9 of the All Document approved by EASA on 21 May 2007. This

statement required to track interchangeable damage tolerant part movements

between aeroplanes.

It has been reported thai some elevators may have been moved from the

aeroplane on which they were originally fitled to another aeroplane, and spare

parts may have been installed kithout being traced with regard to the All

Document requirements. Cons~quently, those elevators might not have been

inspected within the applicable required time frame as per All task 552007

requirements.

For the reasons described above, this AD requires the identification of the

Page 1/4
EASA AD No.: 2010-0091

elevators installed on the aeroplane to determine whether these elevators

have been inspected within the applicable required time frame as per All task

552007. If this has not been done, this AD requires the accomplishment of that

inspection and, depending on findings, associated corrective action(s).

Effective Date: 02 June 2010

Required as indicated:

I

(1) Within 30 days after the effective date of this AD, identify the PIN of the LH

and RH elevators in accordance with the instructions defined in Airbus ,

Service Bulletin (SB) A320-55A1040.

(2) If the first twelve digits of In identified elevator PIN are one of those listed

in Table 1 of this AD, within 30 days after the effective date of this AD,

determine the elapsed (calendar) lime since the elevator first flight after

accomplishment of the instructions of Airbus SB A320-55-1 024 on this

elevator, or the elapsed time since the elevator first flight, as applicable,

and compare it to the threshold for the next due inspection as per AU

tasks 552007-01-1, or 552007-01-3 requirements defined in Airbus All

Document reference AIISE-M4/95A.0252/96 at issue 9.

Table 1

Part name ~/N (first 12 digits only)

LH Elevator q55280001000

RH Elevator 055280001001

(2.1 ) If the elapsed time, determined as required by paragraph (2) of this

AD, has exceeded the All threshold for the next due inspection:

Required Action(s)

Within 30 days after the effective date of this AD, perform the and Compliance

Time(s): special detailed inspection of the affected elevators Top and Bottom

skin panels and apply the associated corrective actions in

accordance with the All tasks 552007-01-1, or 552007-01-3

requirements defined in Airbus All Document reference A1/SEM4/95A.0252/96 at issue 9.

{2.2) If the elapsed time, !determined as required by paragraph (2) of this

AD, has not exceeded the All threshold for the next due inspection

Before reaching tha~ threshold, or within 30 days after the effective

date of this AD, whichever occurs later, perform the special detailed

inspection of the affected elevators Top and Bottom skin panels and

apply the associated corrective actions in accordance with the AU

lasks 552007-01-1, or 552007-01-3 requirements defined in Airbus

All Document reference AI/SE-M4/95A.0252/96 at issue 9.

(2.3) Accomplishment of corrective actions as required by paragraph

(2.1) or (2.2) of this AD, as applicable, does not consUtuie

terminating action for the repetitive inspections of Airbus All

Document reference AI/SE-M4/95A,0252/96 at issue 9.

(3) If the first twelve digits of ah identified elevator PIN are one of those listed

in table 2 of this AD, withinl30 days after the effective date of this AD,

determine the elapsed (cal:endar) time since this elevator first flight and

compare it to the threshold, for the next due inspection as per All tasks

552007-01-2, or 552007-0'-4 requirements defined in Airbus All

Document reference AI/SE-M4/95A.0252/96 at issue 9.

EASA Form 110 Page 214
EASA AD No.: 2010-0091

Table 2

Part name PIN (firs\12 digits only)

LH Elevator D55280q01002, D55280001004, D55280001008,

D55280q01010,or 055280001012

RH Elevator D55280q01003, 055280001005, 055280001009,

D55280q01011,orD55280001013

(3.1 ) If the elapsed time, 1termined as required by paragraph (3) of this

AD, has exceeded thle ALllhreshold for the next due inspection:

Within 30 days after [he effective date of this AD, perform the

special detailed insp~ction of the affecled elevators Top and Bottom

skin panels and apply the associated corrective actions in

accordance with the All tasks 552007-01-2, or 552007-01-4

requirements defined in Airbus All Document reference AI!SEM4J95A.0252!96 at i~sue 9.

(3.2) If the elapsed time, d,etermined as required by paragraph (3) of this

AD, has nol exceede'd the AlIlhreshold for the next due inspection:

Before reaching that ~hreshold, or within 30 days after the effective

date of this AD, whichever occurs later, perform the special detailed

inspection of the affetted elevators Top and Bottom skin panels and

apply the associaledlcorrective actions in accordance with the All

tasks 552007-01-2, or 552007-01-4 requirements defined in Airbus

All Document reference AIJSE-M4/95A.0252/96 at issue 9.

(3.3) Accomplishment of cbrrective actions as required by paragraph

(3.1) or (3_2) of this AD, as applicable, does not constitute

terminating action fo~ the repetitive inspections of Airbus All

Document reference IAI/SE-M4/95A.0252!96 at Issue 9.

I

(4) Aeroplanes on which the LH and RH elevators installed PIN have already

been physically identified and that can be demonstrated from data records

to be compliant with Airbus All Document reference Al/SEM4/95A.0252/96 at issue 9 tequirements. provided those records can be

relied upon for that purpose~ are not concerned by the requirements of the

paragraphs (1), (2) and (3) of this AD.

(5) Aeroplanes that have been belivered with Airbus All Document reference

AI/SE-M4/95A,0252/96 froni issue 9, and on which no movement (from

one aeroplane to another) df the LH or RH elevators has been

accomplished since aeropldne delivery, are not affected by the

requirements of paragraPhS: (1), (2) and (3) of this AD.

(6) After the effective date of this AD, track all interchangeable damage

tolerant part movements between aeroplanes, in accordance with the

specific statement in the Sebion Rules for Compliance Demonstration,

either in paragraph F of the)ALI Document reference AI/SEM4/9SA.0252J96 allssue 10, or in sub paragraph 10 of Chapter 1 11 of

All Document reference AI)rSE-M4J95A.0252J96 at Issue 9, as applicable.

(7) After the effective date of this AD, do not install any elevator listed in

Tables 1 and 2 of this AD oh an aeroplane, uniess it is in compliance with

the requirements of this AD]

I

Airbus A318/A319/A320JA321 AUI Document issue 09, reference AI!SE- AI/SE-

,

Ref. Publications: M4/95A.0252/96 approved bY:1'A on 21 May 2007.

Airbus Service Bulletin A320-55Ar040 at originai issue,

EASA Form 110 Page 314
EASA AD No.: 2010-0091

Airbus Service Bullelln A320-55-1024 at original issue or Revision 01_

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

compliance with the requirements of this AD.

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 publlcation.

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

Directives, Safely Management & Research Section, Certification

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

4. For any question concernill9 the technical content of the requirements in

this AD, please contact:

AIRBUS - Ail"'Northiness Office - EAS; Fax +33 561 934451;

E-mOl il; mOl ilto: accou nLai I"'Nb,1h-eas@airbus.com.

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EASA Form 110 Page 4/r