EASA AD No.: 2009-0141 

EASA Form 110 Page 1/8 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0141 

Date: 02 July 2009 

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 operate an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise 

specified by the Agency [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) exemption]. 

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 : None 

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 Carbon Fiber Reinforced 

Plastic (CFRP) rudders having part numbers (P/N) and serial numbers 

(S/N) as listed in Appendix A 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 the 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 loss of the rudder leads to degradation 

of the handling qualities and reduces the controllability of the aeroplane. 

This AD requires inspections of specific areas and, when necessary, the 

application of corrective actions for those rudders where production reworks 

have been identified.
EASA AD No.: 2009-0141 

EASA Form 110 Page 2/8 

Effective Date: 16 July 2009 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated: 

(1) For rudders with a honeycomb core density of 24 kg/m3 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 01:

(1.1) Reinforced area location: 

Unless already accomplished, within 200 days from the effective 

date of this AD, perform Vacuum Loss inspection on the rudder 

reinforced area in accordance with instructions defined in Airbus 

AOT A320-55A1038 Revision 01. 

(1.2) Trailing edge area location: 

(1.2.1) Unless already accomplished, within 20 months from the 

effective date of this AD, perform Elasticity Laminate Checker 

inspection on the rudder trailing edge area in accordance with 

instructions defined in Airbus AOT A320-55A1038 

Revision 01. 

(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 the 

effective date of this AD, 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 01. 

(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 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 AOT 

A320-55A1038 Revision 01. 

(1.3.4) Accomplishment of the inspection 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. 

(1.4) In case of findings during the inspections defined in paragraphs 

(1.1), (1.2) or (1.3) of this AD, before 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) Within 10 days after accomplishment of each inspection in 

accordance with paragraphs (1.1), (1.2) or (1.3) of this AD, report 
EASA AD No.: 2009-0141 

EASA Form 110 Page 3/8 

the inspection results, including no findings, to Airbus. 

(2) For rudders not having a honeycomb core density of 24 kg/m3

 as 

identified in Appendix A to this AD, apply the following actions for the 

locations defined in Airbus AOT A320-55A1038 Revision 01:

 For the purpose of this AD a Reference Date is defined as the 

effective date of this AD 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 inspection on the rudder 

reinforced area in accordance with instructions defined in Airbus 

AOT A320-55A1038 Revision 01. 

(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 01. 

(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 01. 

(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 the 

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 01. 

(2.3.4) Accomplishment of the inspection required by paragraph (2.3.3) 

of this AD cancels the initial and repetitive 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, before 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) Within 10 days after accomplishment of each inspection in 

accordance with paragraphs (2.1), (2.2) or (2.3) of this AD, report 
EASA AD No.: 2009-0141 

EASA Form 110 Page 4/8 

the results, including no findings, to Airbus. 

(3) All rudders that have passed the inspection, before the effective date 

of this AD, 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, are compliant 

with the associated requirements of this AD for the areas inspected. 

Additional areas requiring inspection are defined in AOT A320-

55A1038 at Revision 01. 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) After the effective date of this AD, no person shall install any rudder 

listed in Appendix A to this AD on an aeroplane, unless in compliance 

with the requirements of this AD. 

Ref. Publications: AIRBUS All Operators Telex A320-55A1038 Revision 01. 

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 & Research Section, Certification 

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

4. For any question concerning the technical 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.: 2009-0141 Appendix A 

EASA Form 110 Page 5/8 

EASA AD No. 2009-0141 Appendix A 1/4 

Rudder P/N Affected rudder S/N 

Core density of 

24 kg/m3

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-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-1565 

D554 71001 000 00 TS-1566 
EASA AD No.: 2009-0141 Appendix A 

EASA Form 110 Page 6/8 

EASA AD No. 2009-0141 Appendix A 2/4 

Rudder P/N Affected rudder S/N 

Core density of 

24 kg/m3

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-2079 

D554 71002 000 00 0001 TS-2083 
EASA AD No.: 2009-0141 Appendix A 

EASA Form 110 Page 7/8 

EASA AD No. 2009-0141 Appendix A 3/4 

Rudder P/N Affected rudder S/N 

Core density of 

24 kg/m3

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-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-2406 

D554 71002 000 00 0002 TS-2461 

D554 71002 000 00 0002 TS-2468 
EASA AD No.: 2009-0141 Appendix A 

EASA Form 110 Page 8/8 

EASA AD No. 2009-0141 Appendix A 4/4 

Rudder P/N Affected rudder S/N 

Core density of 

24 kg/m3

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-3197