EASA AD No.: 2010-0164

EASA Form 110 Page 1/17 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0164

Date: 05 August 2010

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate 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 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Age ncy [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemptio n]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) : A318, A319, A320 and A321 aeroplanes

TCDS Number : EASA.A.064

Foreign AD : Not applicable

Supersedure : This AD supersedes EASA AD 2009-0 141 dated 02 July 2009.



### ATA 55 Stabilizers – Rudder Side Shell Skin – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: AIRBUS A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319 -131, A319-132, A319-133, A320-111, A320-211, A320-212, A320-214, 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, if equipped with rudders having part numbers (P/N) and serial numbers (S/N) as listed in Appendix A, B, C, D, or E to this AD.

Reason: Surface defects were visually detected on the rudder of one A319 and one A321 in-service aeroplane. Investigation has determined that t he defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were a result of de-bonding between the skin and honeycomb core. An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The lo ss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. EASA AD 2009-0141 required inspections of specific ar eas and, when necessary, the application of correcti ve actions for those rudders where production reworks have been identified. This AD retains the requirement s of EASA AD 2009-0 141 (addressing the populations of rudders affected by AO T A320-55-1038), which is superseded, and requires:EASA AD No.: 2010-0164

EASA Form 110 Page 2/17 - a local ultrasonic inspection for re inforced area instead of the local

thermography inspection, which is maintained for non-reinforced areas, and

- additional work performance for r udders on which this thermography

inspection has been performed in the reinforced area, and

- additional work performance for some rudders on which an additional area

requiring inspections is defined. This AD also addresses the populations of rudders affected by AOT A320-55- 1039 and Airbus SB A320-55-1035, A 320-55-1036 and A320-55-1037 which were not included in EASA AD 2009-0141.

Effective Date: 19 August 2010

Required Action(s) and Compliance Time(s): Required as indicated: (1) For rudders with a honeycomb core density of 24 kg/m 3 as identified in Appendix A to this AD, apply the following actions for the locations defined in Airbus All Operators Telex (AOT) A320- 55A1038 Revision 02:

(1.1) Reinforced area location: Unless already accomplished, within 200 days from 16 July 2009 [effective date of AD 2009-0141], per form Vacuum Loss inspection on the rudder reinforced area in accordance with instructions defined in Airbus AOT A320-55A1038 Revision 02.

(1.2) Trailing edge area location:

(1.2.1) Unless already accomplished, within 20 months from 16 July 2009 [effective date of AD 2009-0141], perform Elasticity Laminate Checker inspection on the rudder trailing edge area in accordance with instructions defined in Airbus AOT A320-55A1038 Revision 02. (1.2.2) Repeat two further times the inspection defined in paragraph (1.2.1) of this AD at intervals not to exceed 4 500 flight cycles (FC) but not less than 4 000 FC from the last inspection.

(1.3) Other areas locations (splice/lower rib/upper edge/leading edge/other locations): (1.3.1) Unless already accomplished, within 200 days from 16 July 2009 [effective date of AD 2009-0141], perform Elasticity Laminate Checker inspection on the other areas (splice/lower rib/upper edge/leading edge/other locations) in accordance with instructions defined in Airbus AOT A320-55A1038 Revision 02. (1.3.2) Repeat the inspection defined in paragraph (1.3.1) of this AD at intervals not exceeding 1 500 FC or 200 days from the last inspection, whichever occurs first. (1.3.3) Unless already accomplished, within 20 months from 16 July 2009 [effective date of AD 2009-0141], perform Vacuum Loss inspection on these areas (lower rib/upper edge/leading edge/other locations) in accordance with instructions defined in Airbus AOT A320-55A1038 Revision 02. (1.3.4) Accomplishment of the ins pection required by paragraph (1.3.3) cancels the initial and repetitive inspections required by paragraph (1.3.1) and (1.3.2) of this AD.EASA AD No.: 2010-0164

EASA Form 110 Page 3/17 (1.4) In case of findings during the inspections defined in paragraphs (1.1), (1.2) or (1.3) of this AD, befor e next flight, contact Airbus to get further instructions and apply the associated instructions and corrective actions in accordance with the approved data provided.

(1.5) In case of no findings during the inspection defined in paragraphs (1.1) and (1.3.3) of this AD, before next flight, restore the vacuum loss holes as per the option select ed (temporary restoration with self adhesive patches, temporary restoration with resin or permanent restoration), in accordance with Airbus AOT A320-55A1038 Revision 02 and apply the associated inst ructions until performance of permanent restoration.

(1.6) Within 10 days after accomplishment of each inspection in accordance with paragraphs (1.1), (1.2 ) or (1.3) of this AD, report the inspection results, including no findings, to Airbus.

(2) For rudders not having a honeycomb core density of 24 kg/m 3 as identified in Appendix A to this AD, apply the following actions for the locations defined in Airbus AOT A320-55A1038 Revision 02: For the purpose of the paragraph (2), a Reference Date is 16 July 2009 [effective date of AD 2009-0141] or the date when the rudder will accumulate 20 000 FC from its first installation on an aeroplane, whichever occurs later.

(2.1) Reinforced area location: Unless already accomplished, within 200 days from the Reference Date, perform Vacuum Loss insp ection on the rudder reinforced area in accordance with instructions defined in Airbus AOT A320- 55A1038 Revision 02.

(2.2) Trailing edge area location:

(2.2.1) Unless already accomplished, within 20 months from the Reference Date, perform Elasticity Laminate Checker inspection on the rudder trailing edge area in accordance with instructions defined in Airbus AOT A320-55A1038 Revision 02. (2.2.2) Repeat two further times the inspection defined in paragraph (2.2.1) of this AD at intervals not to exceed 4 500 FC but not less than 4 000 FC from the last inspection.

(2.3) Other areas locations (splice/lower rib/upper edge/leading edge/other locations): (2.3.1) Unless already accomplished, within 200 days from the Reference Date, perform Elasticity Laminate Checker inspection on the other areas (splice/lower rib/upper edge/leading edge/other locations) in accordance with instructions defined in Airbus AOT A320- 55A1038 Revision 02. (2.3.2) Repeat the inspection defined in paragraph (2.3.1) of this AD at intervals not exceeding 1 500 FC or 200 days from the last inspection, whichever occurs first. (2.3.3) Unless already accomplished, within 20 months from theEASA AD No.: 2010-0164

EASA Form 110 Page 4/17 Reference Date, perform Vacuum Loss inspection on these areas (lower rib/upper edge/leading edge/other locations) in accordance with instructions defined in Airbus AOT A320-55A1038 Revision 02. (2.3.4) Accomplishment of the inspec tion required by paragraph (2.3.3) of this AD cancels the initial and re petitive inspections required by paragraph (2.3.1) and (2.3.2) of this AD.

(2.4) In case of findings during the inspections defined in paragraphs (2.1), (2.2) or (2.3) of this AD, befor e next flight, contact Airbus to get further instructions and apply the associated instructions and corrective actions in accordance with the approved data provided.

(2.5) In case of no findings during the inspection defined in paragraphs (2.1) and (2.3.3) of this AD, before next flight, restore the vacuum loss holes as per the option select ed (temporary restoration with self adhesive patches, temporary restoration with resin or permanent restoration), in accordance with Airbus AOT A320-55A1038 Revision 02 and apply the associated inst ructions until performance of permanent restoration.

(2.6) Within 10 days after accomplishment of each inspection in accordance with paragraphs (2.1), (2.2 ) or (2.3) of this AD, report the results, including no findings, to Airbus.

(3) All rudders that have passed the inspection, before 16 July 2009 [effective date of AD 2009-0141], in accordance with the instructions of Airbus AOT A320-55A1038 at original issue or Sampling instruction Technical Disposition (TD) ref. TD/K4/S2/27051/2009 issue B (applicable only to rudder S/N TS-1536, having P/N D554 71000 020 00), are compliant with the associat ed requirements of paragraph (1) or (2) of this AD for the areas inspected. Additional areas requiring inspection are defined in AOT A320-55A1038 at Revision 01 or Revision 02. For these additional areas the requirements of paragraphs (1) or (2) of this AD are applicable. For all areas, the repetitive inspections required by paragraphs (1) or (2) of this AD remain applicable.

(4) All rudders that have passed the insp ection, before the effective date of this AD, in accordance with the instructions of Airbus AOT A320- 55A1038 Revision 01, are compliant wi th the associated requirements of paragraph (1) or (2) of this AD for the areas inspected. Additional areas requiring inspection are defined in AOT A320-55A1038 at Revision 02. For these additional areas the requirements of paragraphs (1) or (2) of this AD are applicable. For all area s, the repetitive inspections required by paragraphs (1) or (2) of this AD remain applicable.

(5) For rudders on which temporary vacuum loss hole restoration with resin or permanent vacuum loss hole restoration has been performed before the effective date of this AD in rein forced area as per paragraph (1.5) or (2.5) of this AD, within 4500 FC from restoration date perform an ultrasonic inspection in accordance with the instructions of Airbus AOT A320-55A1038 Revision 02.

(6) For rudders listed in Appendix B to this AD, apply the followingEASA AD No.: 2010-0164

EASA Form 110 Page 5/17 actions for the locations defined in Airbus AOT A320-55A1039: For the purpose of the paragraph (6), a Reference Date of this AD is the effective date of this AD or the date when the rudder will accumulate 20 000 FC from its first installation on the aeroplane, whichever occurs later,

(6.1) Unless already accomplished, within 20 months from the effective date of this AD or within 200 days from the Reference Date of this AD, whichever occurs first, and depending on the location defined in Airbus AOT A320-55A1039, perform X-Ray and/or Elasticity Laminate Checker (ELCh) and/or vacuum loss and/or thermography inspections, as applicable to rudder P/N and S/N, in accordance with the instructions of paragraph 4.2.2.1.1. of this Airbus AOT A320-55A1039.

(6.2) Within 10 days after the ac complishment of the inspections required by paragraph (6.1) of this AD, send the developed X-Ray films and the film layout arrangement to Airbus.

(6.3) Within 1500 Flight Cycles or 200 days after the accomplishment of the requirements of paragraph (6.1) of this AD, which ever occurs first, as applicable to rudder P/N and S/N:

(6.3.1) Trailing edge area location: (6.3.1.1) Perform ELCh inspection on the rudder trailing edge area in accordance with instructions of paragraph 4.2.2.1.2. of this Airbus AOT A320-55A1039. (6.3.1.2) In case of no findings, repeat two further times the inspection defined in paragraph (6.3.1.1) of this AD at intervals not to exceed 4 500 FC but not less than 4 000 FC from the last inspection.

(6.3.2) Other areas location (lower rib/upper edge/leading edge/other locations): Perform a vacuum loss inspection on the other areas in accordance with instructions of paragraph 4.2.2.1.2. of Airbus AOT A320-55A1039.

(6.4) In case of findings during the inspections defined in paragraph (6.1) and (6.3) of this AD, befor e next flight, contact Airbus for further instructions and apply the associated instructions and corrective actions in accordance with the approved data provided.

(6.5) In case of no findings during the vacuum loss inspection defined in paragraphs (6.1) and (6.3.2) of this AD, before next flight, restore the vacuum loss holes as per the option selected (temporary restoration with self adhesive patches, temporary restoration with resin or permanent restoration) in accordance with Airbus AOT A320-55A1039 and apply the associated instructions until performance of permanent restoration.

(6.6) Within 10 days after accomplishment of each inspection in accordance with paragraphs (6.1) and (6.3) of this AD, report the results, including no findings, to Airbus.EASA AD No.: 2010-0164

EASA Form 110 Page 6/17 (7) For rudders listed in Appendix C to this AD apply the following actions for the locations defined in Airbus AOT A320-55A1039: For the purpose of the paragraph (7), a Reference Date of this AD is the effective date of this AD or the dat e when the rudder will accumulate 20 000 FC from its first installation on the aeroplane, whichever occurs later,

(7.1) For rudders with a honeycomb core density of 24 kg/m3 as identified in Appendix C to this AD, within 200 days from the effective date of this AD, replace the affected rudder in accordance with the instructions of Airbus AOT A320-55A1039.

(7.2) For rudders not having a honeycomb core density of 24 kg/m3 as identified in Appendix C to this AD, within 20 months from the effective date of this AD or 200 days from the Reference Date of this AD, whichever occurs firs t, replace the affected rudder in accordance with the instructions of Airbus AOT A320-55A1039.

(8) For rudders whose P/N and S/N are listed in the Appendix D to this AD, apply the following actions for the locations defined in Airbus Service Bulletin (SB) A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Air bus SB A320-55-1037 Revision 01, as applicable to aeroplane model : (8.1) Reinforced area location: Unless already accomplished, within the compliance time specified in paragraph (8.1.1) or (8.1.2) below, whichever occurs later of § (8.1.1) or (8.1.2), perform Vacuum Loss inspection on the rudder reinforced area in accordance with instructions defined in Airbus SB A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Airbus SB A320-55-1037 Revision 01, as applicable to aeroplane model : (8.1.1) Before the rudder accumulates 17 000 FC since its first installation, without exceeding 20 months from the effective date of this AD, or (8.1.2) Within 200 days after the effective date of this AD.

(8.2) Trailing edge area location:

(8.2.1) Unless already accomplished, within 20 months after the effective date of this AD, perform Elasticity Laminate Checker inspection on the rudder trailing edge area in accordance with instructions defined in Airbus SB A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Airbus SB A320-55-1037 Revision 01, as applicable to aeroplane model. (8.2.2) Repeat two further times the inspection defined in paragraph (8.2.1) of this AD at intervals not to exceed 4 500 FC but not less than 4 000 FC from the last inspection.

(8.3) Other areas locations (splice/lower rib/upper edge/leading edge/other locations): (8.3.1) Unless already accomplish ed, within the compliance time specified in paragraph (8.3.1.1 ) or (8.3.1.2) below, whichever occurs later of the § (8.3.1.1) or (8.3.1.2), perform ElasticityEASA AD No.: 2010-0164

EASA Form 110 Page 7/17 Laminate Checker inspection on t he other areas (splice/lower rib/upper edge/leading edge/other locations) in accordance with instructions defined in Airbus SB A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Airbus SB A320-55- 1037 Revision 01, as applicable to aeroplane model : (8.3.1.1) Before the rudder ac cumulates 17 000 FC since its first installation, without exceeding 20 months from the effective date of this AD, or (8.3.1.2) Within 200 days after the effective date of this AD.

(8.3.2) Repeat the inspection defined in paragraph (8.3.1) of this AD at intervals not exceeding 1 500 FC or 200 days from the last inspection, whichever occurs first. (8.3.3) Unless already accomplished, within 20 months after the effective date of this AD, perform Vacuum Loss inspection on these areas (lower rib/upper edge/leading edge/other locations) in accordance with instructions defined in Airbus SB A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Airbus SB A320-55- 1037 Revision 01, as applicable to aeroplane model. (8.3.4) Accomplishment of the ins pection required by paragraph (8.3.3) cancels the initial and repetitive inspections required by paragraph (8.3.1) and (8.3.2) of this AD.

(8.4) In case of findings during the inspections defined in paragraphs (8.1), (8.2) or (8.3) of this AD, befor e next flight, contact Airbus to get further instructions and apply bef ore next flight the associated instructions and corrective action s in accordance with the approved data provided.

(8.5) In case of no findings during the inspection defined in paragraphs (8.1) and (8.3.3) of this AD, before next flight, restore the vacuum loss holes as per the option select ed (temporary restoration with self adhesive patches, temporary restoration with resin or permanent restoration), in accordance with Airbus SB A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Airbus SB A320-55- 1037 Revision 01, as applicable to aeroplane model, and apply the associated instructions until perform ance of permanent restoration.

(8.6) Within 10 days after accomplishment of each inspection in accordance with paragraphs (8.1), (8.2 ) or (8.3) of this AD, report the inspection results, including no findings, to Airbus. (8.7) Aeroplanes inspected or restored in accordance with the instructions of Airbus SB A320-55-1035 at origi nal issue, or Airbus SB A320-55- 1036 at original issue, or Airbus SB A320-55-1037 at original issue prior to the effective date of this AD, are compliant with the requirements of paragraph (8) of this AD for the inspected area. For all areas, the repetitive inspection s required by paragraph (8) of this AD remain applicable.

(9) For rudders whose P/N and S/N are listed in the Appendix E to this AD, apply the following actions for the locations defined in Airbus SB A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Airbus SB A320-55-1037 Revision 01, as applicable toEASA AD No.: 2010-0164

EASA Form 110 Page 8/17 aeroplane model : (9.1) Unless already accomplished, within 4500 FC but not less than 4 000 FC from the sampling inspection, perform Elasticity Laminate Checker inspection on the rudder trailing edge area in accordance with instructions defined in Airbus SB A320-55-1035 Revision 01, or Airbus SB A320-55-1036 Revision 01, or Airbus SB A320-55-1037 Revision 01, as applicable to aeroplane model. (9.2) Repeat once the inspection defined in paragraph (9.1) of this AD at intervals not to exceed 4 500 FC but not less than 4 000 FC from the last inspection. (9.3) In case of findings during the inspections defined in paragraphs (9.1) or (9.2) of this AD, before next flight, contact Airbus to get further instructions and apply bef ore next flight the associated instructions and corrective action s in accordance with the approved data provided. (9.4) Within 10 days after accomplishment of each inspection in accordance with paragraphs (9.1), (9 .2) or (9.3) of this AD, report the inspection results, including no findings, to Airbus. (9.5) Aeroplanes inspected or restored in accordance with the instructions of Airbus SB A320-55-1035 at origi nal issue, or Airbus SB A320-55- 1036 at original issue, or Airbus SB A320-55-1037 at original issue prior to the effective date of this AD, are compliant with the requirements of paragraph (9) of this AD for the inspected area. For all areas, the repetitive inspection s required by paragraph (9) of this AD remain applicable.

(10) After the effective date of this AD , do not install any rudder listed in Appendix A or B or C or D or E to this AD on an aeroplane, unless in compliance with the requirements of this AD.

Ref. Publications: Airbus All Operators Telex A320-55A1038 Revision 02. Airbus All Operators Telex A320-55A1039 at original issue Airbus Service Bulletin A320-55-1035 at original issue Airbus Service Bulletin A320-55-1036 at original issue Airbus Service Bulletin A320-55-1037 at original issue Airbus Technical Disposition ref. TD/K4/S2/27051/2009 issue B. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks: 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 publication. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the tec hnical content of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EAS; Fax +33 5 61 93 44 51; E-mail: account.airworth-eas@airbus.com

.EASA AD No.: 2010-0164

EASA Form 110 Page 9/17 Appendix A page 1 of 4

Rudder P/N Affected rudder S/N Core density of 24 kg/m 3

D554 71000 010 00 TS-1069 X D554 71000 010 00 TS-1090 X D554 71000 012 00 TS-1227 X D554 71000 014 00 TS-1350 D554 71000 014 00 TS-1366 D554 71000 014 00 TS-1371 D554 71000 014 00 TS-1383 D554 71000 014 00 TS-1387 D554 71000 016 00 TS-1412 D554 71000 018 00 TS-1443 D554 71000 018 00 TS-1444 D554 71000 018 00 TS-1468 D554 71000 020 00 TS-1480 D554 71000 020 00 TS-1491 D554 71000 020 00 TS-1494 D554 71000 020 00 TS-1495 D554 71000 020 00 TS-1498 D554 71000 020 00 TS-1499 D554 71000 020 00 TS-1500 D554 71000 020 00 TS-1505 D554 71000 020 00 TS-1506 D554 71000 020 00 TS-1507 D554 71000 020 00 TS-1509 D554 71000 020 00 TS-1515 D554 71000 020 00 TS-1528 D554 71000 020 00 TS-1530 D554 71000 020 00 TS-1532 D554 71000 020 00 TS-1535 D554 71000 020 00 TS-1536 D554 71000 020 00 TS-1538 D554 71001 000 00 TS-1537 D554 71001 000 00 TS-1540 D554 71001 000 00 TS-1541 D554 71001 000 00 TS-1543 D554 71001 000 00 TS-1548 D554 71001 000 00 TS-1549 D554 71001 000 00 TS-1551 D554 71001 000 00 TS-1554 D554 71001 000 00 TS-1555 D554 71001 000 00 TS-1556 D554 71001 000 00 TS-1557 D554 71001 000 00 TS-1559 D554 71001 000 00 TS-1562 D554 71001 000 00 TS-1563 D554 71001 000 00 TS-1564 D554 71001 000 00 TS-1565EASA AD No.: 2010-0164

EASA Form 110 Page 10/17 Appendix A page 2 of 4

Rudder P/N Affected rudder S/N Core density of 24 kg/m 3

D554 71001 000 00 TS-1566 D554 71001 000 00 TS-1567 D554 71001 000 00 TS-1568 D554 71001 000 00 TS-1569 D554 71001 000 00 TS-1570 D554 71001 000 00 TS-1573 D554 71001 000 00 TS-1575 D554 71001 000 00 TS-1578 D554 71001 000 00 TS-1579 D554 71001 000 00 TS-1580 D554 71001 000 00 TS-1581 D554 71001 000 00 TS-1582 D554 71001 000 00 TS-1584 D554 71001 000 00 TS-1593 D554 71001 000 00 TS-1594 D554 71001 000 00 TS-1596 D554 71001 000 00 TS-1599 D554 71001 000 00 TS-1603 D554 71001 000 00 TS-1609 D554 71001 000 00 TS-1621 D554 71001 000 00 TS-1626 D554 71001 000 00 TS-1627 D554 71001 000 00 TS-1635 D554 71001 000 00 TS-1637 D554 71002 000 00 TS-2306 D554 71002 000 00 0001 TS-2003 D554 71002 000 00 0001 TS-2005 D554 71002 000 00 0001 TS-2013 D554 71002 000 00 0001 TS-2016 D554 71002 000 00 0001 TS-2019 D554 71002 000 00 0001 TS-2020 D554 71002 000 00 0001 TS-2022 D554 71002 000 00 0001 TS-2024 D554 71002 000 00 0001 TS-2026 D554 71002 000 00 0001 TS-2031 D554 71002 000 00 0001 TS-2033 D554 71002 000 00 0001 TS-2043 D554 71002 000 00 0001 TS-2047 D554 71002 000 00 0001 TS-2048 D554 71002 000 00 0001 TS-2054 D554 71002 000 00 0001 TS-2058 D554 71002 000 00 0001 TS-2059 D554 71002 000 00 0001 TS-2064 D554 71002 000 00 0001 TS-2072 D554 71002 000 00 0001 TS-2075 D554 71002 000 00 0001 TS-2076 D554 71002 000 00 0001 TS-2079EASA AD No.: 2010-0164

EASA Form 110 Page 11/17 Appendix A page 3 of 4

Rudder P/N Affected rudder S/N Core density of 24 kg/m 3

D554 71002 000 00 0001 TS-2083 D554 71002 000 00 0001 TS-2089 D554 71002 000 00 0002 TS-2090 D554 71002 000 00 0002 TS-2095 D554 71002 000 00 0002 TS-2103 D554 71002 000 00 0002 TS-2116 D554 71002 000 00 0002 TS-2122 D554 71002 000 00 0002 TS-2133 D554 71002 000 00 0002 TS-2142 D554 71002 000 00 0002 TS-2147 D554 71002 000 00 0002 TS-2157 D554 71002 000 00 0002 TS-2158 D554 71002 000 00 0002 TS-2162 D554 71002 000 00 0002 TS-2167 D554 71002 000 00 0002 TS-2174 D554 71002 000 00 0002 TS-2176 D554 71002 000 00 0002 TS-2181 D554 71002 000 00 0002 TS-2189 D554 71002 000 00 0002 TS-2191 D554 71002 000 00 0002 TS-2203 D554 71002 000 00 0002 TS-2205 D554 71002 000 00 0002 TS-2207 D554 71002 000 00 0002 TS-2212 D554 71002 000 00 0002 TS-2224 D554 71002 000 00 0002 TS-2229 D554 71002 000 00 0002 TS-2233 D554 71002 000 00 0002 TS-2241 D554 71002 000 00 0002 TS-2246 D554 71002 000 00 0002 TS-2249 D554 71002 000 00 0002 TS-2270 D554 71002 000 00 0002 TS-2275 D554 71002 000 00 0002 TS-2289 D554 71002 000 00 0002 TS-2290 D554 71002 000 00 0002 TS-2294 D554 71002 000 00 0002 TS-2309 D554 71002 000 00 0002 TS-2347 D554 71002 000 00 0002 TS-2348 D554 71002 000 00 0002 TS-2349 D554 71002 000 00 0002 TS-2357 D554 71002 000 00 0002 TS-2361 D554 71002 000 00 0002 TS-2380 D554 71002 000 00 0002 TS-2383 D554 71002 000 00 0002 TS-2390 D554 71002 000 00 0002 TS-2394 D554 71002 000 00 0002 TS-2396 D554 71002 000 00 0002 TS-2401 D554 71002 000 00 0002 TS-2406EASA AD No.: 2010-0164

EASA Form 110 Page 12/17 Appendix A page 4 of 4

Rudder P/N Affected rudder S/N Core density of 24 kg/m 3

D554 71002 000 00 0002 TS-2461 D554 71002 000 00 0002 TS-2468 D554 71002 000 00 0002 TS-2516 D554 71002 000 00 0002 TS-2537 D554 71002 000 00 0002 TS-2543 D554 71002 000 00 0002 TS-2546 D554 71002 000 00 0002 TS-2619 D554 71002 000 00 0002 TS-2684 D554 71002 000 00 0003 TS-2752 D554 71002 000 00 0003 TS-2869 D554 71002 000 00 0003 TS-2876 D554 71002 000 00 0003 TS-2970 D554 71002 000 00 0003 TS-2971 D554 71002 000 00 0003 TS-2987 D554 71004 000 00 0000 TS-3083 D554 71004 000 00 0000 TS-3197EASA AD No.: 2010-0164

EASA Form 110 Page 13/17 Appendix B Rudder P/N Affected rudder S/N D554-71000-014-00 TS-1278 D554-71002-000-00-0001 TS-2081 D554-71002-000-00-0002 TS-2125 D554-71002-000-00-0002 TS-2129 D554-71002-000-00-0002 TS-2160 D554-71002-000-00-0002 TS-2201 D554-71002-000-00-0002 TS-2328 D554-71002-000-00-0002 TS-2425 D554-71002-000-00-0002 TS-2511 D554-71002-000-00-0003 TS-2768 D554-71002-000-00-0003 TS-2999 D554-71002-000-00-0003 TS-3004 D554-71002-000-00-0003 TS-3051 D554-71004-000-00-0001 TS-3288

Appendix C

Rudder P/N Affected rudder S/N Core density of 24 kg/m3 D554-71000-008-00 TS-1032 X D554-71000-010-00 TS-1092 X D554-71000-014-00 TS-1314 D554-71000-018-00 TS-1445 D554-71000-020-00 TS-1520 D554-71002-000-00-0001 TS-2037 D554-71002-000-00-0002 TS-2109 D554-71002-000-00-0002 TS-2123 D554-71002-000-00-0002 TS-2124 D554-71002-000-00-0002 TS-2424 D554-71002-000-00-0002 TS-2559 D554-71002-000-00-0003 TS-3061 D554-71004-000-00-0001 TS-3694 D554-71004-000-00-0001 TS-3709 D554-71004-000-00-0002 TS-4148EASA AD No.: 2010-0164

EASA Form 110 Page 14/17 Appendix D

Affected Rudder P/N

D5547100000000 D5547100000200 D5547100000400 D5547100000600 D5547100000800 D5547100001000 D5547100001200 D5547100001400 D5547100001600 D5547100001800 D5547100002000 D5547100100000 D5547100200000 D5547100300000 D5547100400000

Appendix D - Associated S/N - page 1 of 3 TS-1368 TS-1616 TS-2080 TS-2159 TS-2222 TS-2276 TS-2327 TS-1389 TS-1619 TS-2082 TS-2163 TS-2223 TS-2279 TS-2330 TS-1496 TS-1622 TS-2084 TS-2168 TS-2227 TS-2280 TS-2331 TS-1501 TS-1632 TS-2085 TS-2169 TS-2228 TS-2281 TS-2332 TS-1503 TS-1639 TS-2086 TS-2170 TS-2230 TS-2284 TS-2333 TS-1508 TS-2004 TS-2094 TS-2172 TS-2231 TS-2285 TS-2334 TS-1516 TS-2008 TS-2096 TS-2175 TS-2232 TS-2286 TS-2336 TS-1527 TS-2010 TS-2097 TS-2177 TS-2234 TS-2293 TS-2337 TS-1529 TS-2012 TS-2098 TS-2179 TS-2235 TS-2297 TS-2338 TS-1534 TS-2014 TS-2100 TS-2182 TS-2236 TS-2298 TS-2339 TS-1545 TS-2017 TS-2101 TS-2183 TS-2238 TS-2299 TS-2340 TS-1547 TS-2018 TS-2106 TS-2185 TS-2240 TS-2302 TS-2341 TS-1553 TS-2023 TS-2113 TS-2192 TS-2242 TS-2303 TS-2343 TS-1560 TS-2025 TS-2115 TS-2193 TS-2244 TS-2304 TS-2346 TS-1561 TS-2029 TS-2118 TS-2195 TS-2245 TS-2305 TS-2352 TS-1571 TS-2032 TS-2126 TS-2199 TS-2248 TS-2307 TS-2353 TS-1572 TS-2034 TS-2130 TS-2200 TS-2250 TS-2310 TS-2354 TS-1574 TS-2039 TS-2131 TS-2204 TS-2251 TS-2311 TS-2355 TS-1576 TS-2040 TS-2132 TS-2206 TS-2252 TS-2312 TS-2356 TS-1577 TS-2041 TS-2134 TS-2208 TS-2254 TS-2313 TS-2358 TS-1583 TS-2046 TS-2136 TS-2209 TS-2258 TS-2315 TS-2360 TS-1585 TS-2050 TS-2140 TS-2210 TS-2259 TS-2316 TS-2362 TS-1588 TS-2051 TS-2143 TS-2211 TS-2260 TS-2319 TS-2363 TS-1591 TS-2052 TS-2144 TS-2213 TS-2261 TS-2320 TS-2364 TS-1600 TS-2053 TS-2145 TS-2216 TS-2262 TS-2321 TS-2365 TS-1602 TS-2056 TS-2149 TS-2217 TS-2265 TS-2322 TS-2366 TS-1607 TS-2060 TS-2152 TS-2218 TS-2268 TS-2323 TS-2367 TS-1608 TS-2069 TS-2154 TS-2220 TS-2271 TS-2325 TS-2370 TS-1614 TS-2070 TS-2155 TS-2221 TS-2272 TS-2326 TS-2371EASA AD No.: 2010-0164

EASA Form 110 Page 15/17 Appendix D - Associated S/N - page 2 of 3 TS-2372 TS-2483 TS-2583 TS-2665 TS-2743 TS-2813 TS-2878 TS-2373 TS-2484 TS-2584 TS-2666 TS-2744 TS-2814 TS-2879 TS-2374 TS-2486 TS-2585 TS-2667 TS-2745 TS-2815 TS-2880 TS-2377 TS-2488 TS-2586 TS-2668 TS-2747 TS-2816 TS-2881 TS-2381 TS-2491 TS-2587 TS-2671 TS-2749 TS-2818 TS-2882 TS-2382 TS-2493 TS-2590 TS-2674 TS-2751 TS-2819 TS-2885 TS-2387 TS-2494 TS-2591 TS-2675 TS-2753 TS-2821 TS-2886 TS-2388 TS-2498 TS-2592 TS-2676 TS-2754 TS-2822 TS-2890 TS-2392 TS-2499 TS-2593 TS-2677 TS-2755 TS-2823 TS-2891 TS-2393 TS-2501 TS-2596 TS-2679 TS-2756 TS-2824 TS-2892 TS-2395 TS-2505 TS-2597 TS-2680 TS-2757 TS-2826 TS-2893 TS-2397 TS-2506 TS-2601 TS-2681 TS-2758 TS-2827 TS-2896 TS-2398 TS-2508 TS-2602 TS-2682 TS-2759 TS-2828 TS-2897 TS-2399 TS-2510 TS-2603 TS-2683 TS-2760 TS-2830 TS-2898 TS-2407 TS-2512 TS-2605 TS-2685 TS-2762 TS-2831 TS-2899 TS-2408 TS-2514 TS-2606 TS-2688 TS-2765 TS-2832 TS-2900 TS-2409 TS-2517 TS-2611 TS-2689 TS-2771 TS-2833 TS-2903 TS-2410 TS-2518 TS-2612 TS-2691 TS-2772 TS-2834 TS-2904 TS-2411 TS-2521 TS-2614 TS-2695 TS-2773 TS-2835 TS-2906 TS-2412 TS-2522 TS-2615 TS-2697 TS-2775 TS-2836 TS-2907 TS-2415 TS-2527 TS-2616 TS-2698 TS-2776 TS-2837 TS-2908 TS-2417 TS-2529 TS-2617 TS-2699 TS-2778 TS-2838 TS-2909 TS-2421 TS-2532 TS-2620 TS-2700 TS-2779 TS-2839 TS-2910 TS-2422 TS-2536 TS-2625 TS-2701 TS-2780 TS-2840 TS-2911 TS-2423 TS-2540 TS-2626 TS-2707 TS-2782 TS-2843 TS-2913 TS-2427 TS-2544 TS-2628 TS-2710 TS-2783 TS-2844 TS-2914 TS-2428 TS-2545 TS-2629 TS-2711 TS-2784 TS-2845 TS-2916 TS-2435 TS-2547 TS-2630 TS-2712 TS-2785 TS-2846 TS-2917 TS-2437 TS-2551 TS-2631 TS-2713 TS-2786 TS-2848 TS-2919 TS-2440 TS-2552 TS-2632 TS-2714 TS-2788 TS-2849 TS-2920 TS-2444 TS-2553 TS-2634 TS-2716 TS-2790 TS-2850 TS-2922 TS-2446 TS-2554 TS-2635 TS-2717 TS-2791 TS-2851 TS-2923 TS-2447 TS-2555 TS-2636 TS-2719 TS-2792 TS-2852 TS-2924 TS-2453 TS-2558 TS-2637 TS-2722 TS-2793 TS-2853 TS-2925 TS-2455 TS-2562 TS-2640 TS-2724 TS-2794 TS-2854 TS-2927 TS-2458 TS-2563 TS-2641 TS-2725 TS-2795 TS-2855 TS-2928 TS-2460 TS-2566 TS-2642 TS-2726 TS-2796 TS-2856 TS-2929 TS-2463 TS-2568 TS-2644 TS-2727 TS-2797 TS-2857 TS-2930 TS-2466 TS-2570 TS-2647 TS-2728 TS-2799 TS-2860 TS-2932 TS-2467 TS-2571 TS-2648 TS-2732 TS-2801 TS-2861 TS-2933 TS-2471 TS-2572 TS-2650 TS-2734 TS-2803 TS-2862 TS-2934 TS-2472 TS-2573 TS-2651 TS-2735 TS-2804 TS-2863 TS-2935 TS-2474 TS-2574 TS-2653 TS-2736 TS-2805 TS-2864 TS-2937 TS-2476 TS-2575 TS-2656 TS-2738 TS-2807 TS-2865 TS-2938 TS-2477 TS-2576 TS-2657 TS-2739 TS-2808 TS-2868 TS-2939 TS-2478 TS-2579 TS-2658 TS-2740 TS-2810 TS-2872 TS-2943 TS-2481 TS-2580 TS-2659 TS-2741 TS-2811 TS-2874 TS-2944 TS-2482 TS-2581 TS-2662 TS-2742 TS-2812 TS-2877 TS-2946EASA AD No.: 2010-0164

EASA Form 110 Page 16/17 Appendix D - Associated S/N - page 3 of 3 TS-2948 TS-3040 TS-3113 TS-3177 TS-3249 TS-3689 TS-3928 TS-2949 TS-3043 TS-3114 TS-3178 TS-3250 TS-3690 TS-3936 TS-2950 TS-3046 TS-3116 TS-3179 TS-3251 TS-3695 TS-3939 TS-2951 TS-3049 TS-3119 TS-3180 TS-3252 TS-3699 TS-3942 TS-2953 TS-3050 TS-3120 TS-3181 TS-3253 TS-3702 TS-3950 TS-2954 TS-3052 TS-3121 TS-3182 TS-3255 TS-3703 TS-3958 TS-2955 TS-3054 TS-3122 TS-3183 TS-3256 TS-3704 TS-3961 TS-2957 TS-3055 TS-3123 TS-3184 TS-3257 TS-3706 TS-3968 TS-2958 TS-3056 TS-3124 TS-3185 TS-3259 TS-3708 TS-3987 TS-2959 TS-3058 TS-3125 TS-3186 TS-3262 TS-3710 TS-3993 TS-2960 TS-3060 TS-3126 TS-3188 TS-3271 TS-3717 TS-3995 TS-2962 TS-3065 TS-3127 TS-3189 TS-3276 TS-3718 TS-4003 TS-2964 TS-3066 TS-3129 TS-3191 TS-3278 TS-3734 TS-4027 TS-2965 TS-3071 TS-3131 TS-3193 TS-3282 TS-3743 TS-4031 TS-2968 TS-3072 TS-3132 TS-3194 TS-3286 TS-3761 TS-4087 TS-2969 TS-3074 TS-3133 TS-3195 TS-3289 TS-3772 TS-4099 TS-2973 TS-3075 TS-3134 TS-3198 TS-3290 TS-3780 TS-4118 TS-2976 TS-3076 TS-3135 TS-3200 TS-3291 TS-3789 TS-4145 TS-2980 TS-3077 TS-3138 TS-3201 TS-3292 TS-3805 TS-4146 TS-2984 TS-3078 TS-3139 TS-3202 TS-3295 TS-3820 TS-4147 TS-2985 TS-3079 TS-3140 TS-3204 TS-3297 TS-3821 TS-4163 TS-2986 TS-3080 TS-3141 TS-3205 TS-3306 TS-3822 TS-4167 TS-2988 TS-3081 TS-3142 TS-3207 TS-3309 TS-3824 TS-4175 TS-2991 TS-3082 TS-3143 TS-3210 TS-3310 TS-3825 TS-4178 TS-2998 TS-3084 TS-3144 TS-3215 TS-3317 TS-3839 TS-4181 TS-3001 TS-3087 TS-3145 TS-3216 TS-3320 TS-3841 TS-4186 TS-3002 TS-3088 TS-3148 TS-3217 TS-3328 TS-3843 TS-4195 TS-3003 TS-3089 TS-3149 TS-3218 TS-3388 TS-3844 TS-4212 TS-3005 TS-3090 TS-3151 TS-3219 TS-3392 TS-3846 TS-4232 TS-3006 TS-3091 TS-3154 TS-3221 TS-3395 TS-3849 TS-4271 TS-3009 TS-3093 TS-3155 TS-3222 TS-3429 TS-3850 TS-4331 TS-3011 TS-3094 TS-3156 TS-3223 TS-3441 TS-3851 TS-4345 TS-3016 TS-3096 TS-3158 TS-3224 TS-3516 TS-3853 TS-4366 TS-3018 TS-3097 TS-3159 TS-3226 TS-3561 TS-3855 TS-4396 TS-3020 TS-3098 TS-3160 TS-3227 TS-3567 TS-3857 TS-4401 TS-3021 TS-3100 TS-3161 TS-3232 TS-3574 TS-3860 TS-4420 TS-3025 TS-3101 TS-3162 TS-3234 TS-3590 TS-3862 TS-4461 TS-3026 TS-3102 TS-3164 TS-3235 TS-3591 TS-3863 TS-4480 TS-3027 TS-3103 TS-3166 TS-3236 TS-3595 TS-3871 TS-4636 TS-3028 TS-3104 TS-3167 TS-3237 TS-3598 TS-3878 TS-4651 TS-3030 TS-3105 TS-3168 TS-3240 TS-3609 TS-3879 TS-4678 TS-3031 TS-3106 TS-3169 TS-3241 TS-3625 TS-3882 TS-4696 TS-3032 TS-3107 TS-3170 TS-3242 TS-3638 TS-3883 TS-4770 TS-3033 TS-3108 TS-3171 TS-3243 TS-3650 TS-3885 TS-3034 TS-3109 TS-3172 TS-3244 TS-3669 TS-3910 TS-3035 TS-3110 TS-3174 TS-3245 TS-3684 TS-3914 TS-3037 TS-3111 TS-3175 TS-3247 TS-3685 TS-3921 TS-3038 TS-3112 TS-3176 TS-3248 TS-3687 TS-3924EASA AD No.: 2010-0164

EASA Form 110 Page 17/17 Appendix E

Affected Rudder P/N

D5547100000000 D5547100000200 D5547100000400 D5547100000600 D5547100000800 D5547100001000 D5547100001200 D5547100001400 D5547100001600 D5547100001800 D5547100002000 D5547100100000 D5547100200000 D5547100300000 D5547100400000

Associated S/N TS-2141 TS-2269 TS-2274 TS-2295 TS-2317 TS-2664 TS-2715