## EASA EASA AD No_:2010-0091 

## AIRWORTHINESS DIRECTIVE
AD No.:2010·0091

Date: 19May2010 

# J

Note: This Airworthiness Direct; e (AD) is Issued by EASA. acting in accordance with Regulation (EC) No21612008on bkhatf ofthe European Community, ItsMember Slates and of the European third countries !hOltparticipate in the activities of EASA underArticle 66 of that Regulation. This AD is issued in accordance with EC 1702/2003. Part 21A.3B. In accordance with EC 204212003Anne)!.I. Part MA301, the conlinuing airworthiness otan aircraft shall heensured byaccomplishing any applicable ADs GonsequenUy. no persoll may operate an aircraft towhich anAD applies. except in acwrdance with the requirements ofthatAD, unless otherwise specified bythe Agency [EG204212003Annex I,PartM.A.303}oragreed withtheAuthority ofthe Slateof Registry{EG21612008,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

ATA55 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 ofA318/ 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 7approved 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. Aspecific statement related tothe interchangeable parts policy was introduced in issue 9 ofthe All Document approved by EASA on 21 May 2007. This statement required totrack interchangeable damage tolerant part movements between aeroplanes. Ithas 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 tothe 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 1/4EASAADNo.: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. Ifthis has not been done, this AD requires the accomplishment of that inspection and, depending onfindings, associated corrective action(s).
Effective Date: 02 June 2010 Required as indicated: 

### I (1) Within 30 days after the effective date ofthis AD, identify the PIN ofthe LH and RH elevators in accordance with the instructions defined inAirbus



## , Service Bulletin (SB) A320-55A1040. (2) Ifthe first twelve digits of In identified elevator PIN are one ofthose listed inTable 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 ofthe instructions ofAirbus SB A320-55-1 024 on this elevator, or the elapsed time since the elevator first flight, as applicable, and compare ittothe threshold forthe next due inspection as per AU tasks 552007-01-1, or552007-01-3 requirements defined in Airbus All Document reference AIISE-M4/95A.0252/96 at issue 9.

Table 1 Part name ~/N(first 12digits only) LH Elevator q55280001000 RH Elevator 055280001001

(2.1 ) Ifthe elapsed time, determined as required by paragraph (2) ofthis AD, has exceeded the All threshold forthe next due inspection: Required Action(s) Within 30 days after the effective date ofthis 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) Ifthe 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, orwithin 30 days after the effective date of this AD, whichever occurs later, perform the special detailed inspection ofthe affected elevators Top and Bottom skin panels and apply the associated corrective actions in accordance with the AU lasks 552007-01-1, or552007-01-3 requirements defined inAirbus 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) ofthis AD, as applicable, does not consUtuie terminating action for the repetitive inspections ofAirbus All Document reference AI/SE-M4/95A,0252/96 at issue 9.
(3) Ifthe first twelve digits of ah identified elevator PIN are one ofthose listed intable 2 ofthis AD, withinl30 days after the effective date ofthis AD, determine the elapsed (cal:endar) time since this elevator first flight and compare ittothe threshold, for the next due inspection as per All tasks 552007-01-2, or552007-0'-4 requirements defined in Airbus All Document reference AI/SE-M4/95A.0252/96 at issue 9.

EASAForm 110 Page 214EASA 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 ) Ifthe elapsed time, 1termined as required by paragraph (3) ofthis AD, has exceeded thleALllhreshold for the next due inspection: Within 30 days after [he effective date ofthis AD, perform the special detailed insp~ction ofthe 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) Ifthe elapsed time, d,etermined as required by paragraph (3) ofthis AD, has nol exceede'd the AlIlhreshold for the next due inspection: Before reaching that ~hreshold, orwithin 30 days after the effective date ofthis AD, whichever occurs later, perform the special detailed inspection ofthe affetted elevators Top and Bottom skin panels and apply the associaledlcorrective actions in accordance with the All tasks 552007-01-2, or552007-01-4 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)ofthis AD, as applicable, does not constitute terminating action fo~the repetitive inspections ofAirbus 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 9tequirements. provided those records can be relied upon forthat purpose~ are not concerned bythe requirements ofthe 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) dfthe LH or RH elevators has been accomplished since aeropldne delivery, are not affected bythe requirements of paragraPhS: (1), (2) and (3) of this AD. (6) After the effective date ofthis 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 Fofthe)ALI Document reference AI/SEM4/9SA.0252J96 allssue 10, or in sub paragraph 10of Chapter 1 11 of All Document reference AI)rSE-M4J95A.0252J96 at Issue 9, as applicable. (7) After the effective date ofthis AD, do not install any elevator listed in Tables 1 and 2 ofthis AD oh an aeroplane, uniess it is incompliance 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 May2007. Airbus Service Bulletin A320-55Ar040 atoriginai issue,

EASA Form 110 Page 314EASA AD No.: 2010-0091 Airbus Service Bullelln A320-55-1024 atoriginal issue or Revision 01_ The use of later approved revisions ofthese documents is acceplable for compliance with the requirements of this AD.
1. Ifrequested 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 tothe Airworthiness Directives, Safely Management & Research Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu. 

### 4. For any question concernill9 the technical content ofthe requirements in this AD, please contact: AIRBUS

- Ail"'Northiness Office

- EAS; Fax +33 561 934451; E-mOl il; mOlilto:accou nLaiI"'Nb,1h-ea s@airbus.com.

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EASA Form 110 Page

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