EASA AD No.: 20 1 4

- 0058

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 4 - 0058

Date: 11 March 2014

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 EU 748/2012, Part 21.A.3B. In accordan ce 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 ope rate 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]

. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not Applicable Supersedure: None



### ATA 32 Landing Gear

– Main Landing Gear Sliding Tube Axles

– Inspection

Manufacturer(s): Ai rbus (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

- 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 aeroplanes, all manufacturer se rial numbers (MSN)

. Reason: A m ain l anding g ear (MLG) sliding tube axle rupture occurred in service. Investigation of the affected part show ed that this failure was due to an abnormal grinding operation during overhaul by a certain maintenance and repair organisation located in Singapore

. A population of MLG sliding tubes w a s subsequently identified whose axles may have been subject to this g rinding operati on , which may have resulted in areas of residual stress on the axles on the MLG sliding tubes. In addition, the MSN of the aeroplanes which are known to have had the affected parts installed have been identified. This condition, if not detected and corrected , could lead to cracks in the axle and ( partial ) detachment of axle and wheel from the sliding tube , possibly resulting in fail u re of a MLG with consequent damage to the aeroplane and injury to occupants

. To address this potential unsafe condition, Messier

- Bugatti

- Dowty, the MLG gear manufacturer , issued Service Bulletin ( SB ) 200

- 32

- 313 and SB 201

- 32

- 62 , providing inspection instructions and criteria for removal from service of the affected MLG sliding tubes

. For the reasons describe d above, this AD requires a one

- time S pecial Detail ed I nspection (SDI) of the axle on the affected MLG sliding tubes and, depending on findings, replacement of the MLG sliding tube

.EASA AD No.: 20 1 4

- 0058

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: 25 March 2014 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 3 months after the effective date of this AD, accomplish the following actions: (1.1) I dentify the Part Number (P/N) and Serial Number (S/N) of the MLG sliding tubes installed on each aeroplane. A review of aeroplane maintenance records is acceptable to accomplish the identification as required by this paragraph, provided those records can be relied upon for that purpose. A n a eroplane with an MSN not listed in Table 1 of this AD is not affected by the requirement s of paragraphs (1.2) and (2) o f this AD , provided it can be determined that no MLG sliding tube having a P/N and S/N as listed in Appendix 1 of this AD ha s been installed on that aeroplane since first entry into service

. ( 1. 2) For e a ch MLG sliding tube , identified as required by paragraph (1 .1 ) of this AD, having a P/N and S/N as listed in Appendix 1 of this AD, accomplish a SDI of the affected MLG axle and brake flange in accordance with the instructions of Messier

- Dowty SB 200

- 32

- 313 (A318, A319 and A320) or SB 201

- 32

- 62 (A321), as applicable , or in accordance with the instructions of Airbus SB A320

- 32

- 1416

. ( 2 ) If , during the SDI as required by paragraph ( 1. 2) of this AD, any damage is detected , before next flight, replace the MLG sliding tube with a serviceable one in accordance with the instructions of Messier

- Dowty SB 200

- 32

- 313 (A318, A319 and A320) or SB 201

- 32

- 62 (A321), as applicable , or in accordance with the instructions of Airbus SB A320

- 32

- 1416

. Note: For the purpose of this AD, a serviceable sliding tube is a sliding tube having a P/N and S/N not listed in Appendix 1 of this AD, or a sliding tube having a P/N and S/N listed in Appendix 1 of this A D which has passed the SDI as required by paragraph ( 1. 2) of this AD.

Table 1

– Affected Aeroplanes listed by MSN 0179 0214 0296 0412 0558 0604 0607 0668 0704 0720 0726 0731 0754 0771 0799 0828 0841 0855 0909 0914 0925 0939 0986 1028 1030 1041 1070 1083 1093 1098 1108 1148 1294 1356 2713 2831

( 3 ) Do not install on any aeroplane a MLG sliding tube, having a P/N and S/N as listed in Appendix 1 of this AD , as required by paragraph ( 3 .1) or ( 3 .2) of this AD, as applicable , unless that sliding tube has passed the SDI as required by paragraph ( 1. 2) of this AD

. ( 3 .1) For aeroplanes that have a MLG sliding tube installed , having a P/N and S/N as listed in Appendix 1 of this AD : A fter release to service of the aeroplane following the SDI as required by paragraph ( 1. 2) of this AD

. ( 3 .2) For aeroplanes that, on the effective date of this AD, do not have a MLG sliding tube installed having a P/N and S/N as listed in Appendix 1 of this AD : From the effective date of this AD.EASA AD No.: 20 1 4

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- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Ref. Public ations: Messier

- Dowty SB 200

- 32

- 313 dated 25 February 2013. Messier

- Dowty SB 201

- 32

- 62 dated 25 February 2013

. Airbus SB A320

- 32

- 1416 dated 10 March 2014. The use of later approved revisions o f th e s e document s 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. This AD was posted on 17 January 2014 as PAD 14

- 012 for consultation until 14 February 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conte nt of the requirements in this AD, please contact: AIRBUS

– Airworthiness Office

– EIAS, Fax +33 5 61 93 44 51, E

- mail: account.airworth

- eas@airbus.com

.EASA AD No.: 20 1 4

- 0058

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

### Appendix 1

– A ffected MLG Sliding TubesEASA AD No.: 20 1 4

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TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 5 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

### Appendix 1

– Affected MLG Sliding Tubes (continued)