E ASA AD No.: 20 1 5 - 000 1 R1

TE. CAP.0011 0 - 00 4 © 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 5 - 000 1 R1

Date: 1 5 January 2015 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 E U 748/2012 , Part 21

. A.3B. In accordan ce with E U 1321 /20 14 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 [ EU 1321/2014 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 Revision : This AD revises EASA AD 2015 - 0001 dated 05 January 2015, which supersede d

EASA AD 2014 - 0096 dated 23 April 2014

. 

### ATA 52 Doors – Main Landing Gear Fixed Fairing Assembly – 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 - 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 serial numbers

. Reason: Several occurrences of in - flight loss of main landing gear ( MLG ) fixed and hinge d fairings were reported. The majority of reported events occurred following scheduled maintenance activities. One result of the investigation was that a discrepancy between the drawing and the maintenance manuals was discovered. The mainte nance documents were corrected to prevent mis rigging of the MLG fixed and hinge d fairings , which could induce fatigue cracking. Airbus issued Service Bulletin (SB) A320 - 52 - 1083, providing instructions for a one - time inspection of the MLG fixed fairing com posite insert and the surrounding area, replacement of the adjustment studs at the lower forward position and adjustment to the new clearance tolerances. That SB was replaced by Airbus SB A320 - 52 - 1100 (mod 27716) introducing a re - designed location stud, ro d end and location plate at the forward upper and lower leg fixed - fairing positions. Subsequently, reports were received of post - mod 27716 / post - SB A320 - 52 - 1100 MLG fixed fairing assemblies with corrosion, which could also induce cracking. Thi s condition, if not detected and corrected, could lead to further cases of in flight detachment of a MLG fixed fairing, possibly resulting in injury to personsE ASA AD No.: 20 1 5 - 000 1 R1

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. on the ground and/or damage to the aeroplane. To address this potential unsafe condition, EASA i ssued AD 2014 - 0096 to require repetitive detailed inspection s (DET) of the MLG fixed fairings, and, depending on findings , accomplishment of applicable corrective actions

. Th at AD also prohibited installati on of certain MLG fixed fairing rod end assemblies and studs as replacement parts on aeroplane s incorporating Airbus mod 27716 in production, or modified in accordance with Airbus SB A320 - 52 - 1100 (any revision) in service. Since EASA AD 2014 - 0096 was issued, Airbus developed an alternative inspection prog ram me to meet the AD requirements . In addition, a terminating action (mod 155648) was developed, which is to be made available for in service aeroplanes through Airbus SB A320 - 52 - 1165. Prompted by these developments , EASA issued AD 2015 - 0001, retain ing the requiremen ts of EASA AD 2014 - 0096, which wa s superseded, and add ing an optional terminating action for the repetitive inspections. For post - mod aeroplanes, i.e. incorporating Airbus mod 155648 in production , or modified by Airbus SB A320 - 52 - 1165 in se rvice, the only remaining requirement is to ensure that pre - mod components are no longer installed

. Since that AD was issued, it was discovered that a certain plate support , Part Number ( P/N ) D5285600620000 as listed in T able 3 of the AD , remains part of the post SB A320 - 52 - 1165 configuration and is therefore not affected by any prohibition of installation

– paragraph (11) of the AD

. In addition, an error was detected in Table 1 of the AD (missing P/N plate support ) and paragraph ( 9 ) w as found to be incorrectly worded. For the reasons described above, this AD is revised to introduce the necessary corrections. Effective Date: Revision 1: 19 January 2015 (same as original issue) Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) For aeroplanes in pre - mod 27716 and pre - SB A320 - 52 - 1100 configuration, having components installed as identified by P/N in Table 1 of this AD, within the compliance time as specified in T able 2 of this AD, and, thereafter, at intervals not exceeding 6 500 f light c ycles (FC), replace both right hand ( RH) and left hand (LH) MLG fixed fairing upper and lower attachment studs in accordance with the instructions of Airbus SB A320 - 52 - 1163. Table 1

– P re - mod 27716 (pre - SB A320 - 52 - 1100) C omponents

Part Name P / N Plate - Support D5284024820000 D5284024820200 Stud - Adjustment D5284024420000 Rod end assembly ( lower ) D5284000500000 Rod end assembly ( upper ) D5284000600000E ASA AD No.: 20 1 5 - 000 1 R1

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. Table 2

– Initial Inspection for Pre - mod 27716 A eroplanes Compliance time (whichever occurs later, A , B , C or D ) A Before exceeding 6 500 FC since aeroplane first flight B Within 6 500 FC sin ce last installation of the pre - mod 27716 stud on an aeroplane C Within 1 500 FC after 07 May 2014 [ the effective date of EASA AD 2014 - 0096] D Within 8 months after 07 May 2014 [ the effective date of EASA AD 2014 - 0096] (2) For aeroplanes in post - mod 27716 (or post - Airbus SB A320 - 52 - 1100) configuration, having components installed as identified by P/N in Table 3 of this AD, within the compliance time a s specified in T able 4 of this AD, and, thereafter, at intervals not exceeding 12 months (except as specified in paragraph (4) of this AD) , accomplish a DET of each forward s tud assembly, both RH and LH MLG, in accordance with the instructions of Airbus SB A320 - 52 - 1163. Table 3

– Post - mod 27716 (post - SB A320 - 52 - 1100) C omponents

Part Name P / N D eleted D eleted Stud

– Adjustment D5285600720000 Rod end assembly ( lower ) D5285600400000 Rod end assembly ( upper ) D5285600500000 When, following any DET as required by this paragraph, both RH and LH MLG forward stud assembl ies on an aeroplane are replaced with new ones , the next DET for that aeroplane can be deferred up to 72 months after replacement. Table 4

– Initial Inspection for Post - mod 27716 A eroplanes Compliance time (whichever occurs later, A , B , C or D ) A B efore exceeding 72 months since aeroplane first flight B Within 72 months since last installation of the stud post - mod 27716 or since Airbus SB A320 - 52 - 1100 accomplishment C Within 1 500 FC after 07 May 2014 [the effective date of EASA AD 2014 - 0096] D Within 8 months after 07 May 2014 [the effective date of EASA AD 2014 - 0096] (3) If, during any DET as required by paragraph (2) of this AD, any crack, damage or corrosion (except as specified in paragraph (4) of this AD) is found, before next flight, replace the upper and lower RH and LH MLG fixed fairing forward attachment assemblies in accordance with the instructions of Airbus SB A320 - 52 - 1163 , or in accordance with the instructions of SB A320 - 52 - 1165.E ASA AD No.: 20 1 5 - 000 1 R1

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 4 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. (4) In case corrosion is found on any MLG fixed fairing forward attachment stud assembly (upper, lower, LH or RH) , but the corroded stud is not loose, accomplish the action(s) as specified in paragraph (4.1) or (4.2) of this AD. (4.1) Before next flight, replace the affected assembly in accordance with the instructions of Airbus SB A320 - 52 - 1163 , or in accordance with the instructions of SB A320 - 52 - 1165

. (4.2) Within 4 months after finding corrosion and, thereafter, at intervals not exceeding 4 months , accomplish a DET (same inspection as specified in paragraph (2) of this AD

– reduced intervals) of th e forward stud ass embly of the affected ( RH or LH ) MLG in accordance with the instructions of Airbus SB A320 - 52 - 1163. (5) If, during any DET as required by paragraph ( 4. 2) of this AD, any crack or damage is found, before next flight, replace the affected ( RH or LH ) MLG fixed fairi ng forward attachment assembly in accordance with the instructions of Airbus SB A320 - 52 - 1163, or in accordance with the instructions of SB A320 - 52 - 1165. ( 6 ) Replacement of components on an aeroplane with components as listed in Table 1 or T able 3 of this AD, as required by paragraph (1) , (3) , (4.1), or (5) of this AD , as applicable, does not constitute terminating action for the repetitive DET required by this AD for that aeroplane , except as specified in paragraph (9) of this AD

. (7) Modification of an aeroplane to post - mod 27716 configuration in accordance with the instructions of Airbus SB A320 - 52 - 1100 constitutes terminating action for the repetitive replacements as required by paragraph (1) of this AD for that aeroplane. Refer to p aragraph (2) of this AD to determine the next due DET after modification and the applicable repetitive DET interval. (8) An aeroplane on which Airbus mod 155648 has been embodied in production is not affected by the requirements of paragraphs (1) t hr o ugh ( 5) of this AD , provided that no affected component , identified by P / N as listed in Table 1 or Table 3 of this AD, ha s been installed on that aeroplane since Airbus date of manufacture

. (9) Modification of an aeroplane in accordance with the instructions of Airbus SB A320 - 52 - 11 65 constitutes terminating action for the require ments of paragraphs (1) through (5) of this AD for that aeroplane. ( 10 ) Do not install on any aeroplane a component as listed in Table 1 of this AD, as required by paragraph ( 10 .1) or ( 10.2) of this AD, as applicable. ( 10 .1) For aeroplanes in pre - mod 27716 and pre - SB A320 - 52 - 1100 configuration : After optional modification as specified in paragraph ( 7 ) of this AD. ( 10 .2) For aeroplanes in post - mod 27716 or post - SB A320 - 52 - 1100 configuration : From the effective date of this AD. (11) Do not install on any aeroplane a component as listed in Table 1 or Table 3 of this AD, as required by paragraph ( 11 .1) or ( 11 .2) of this AD, as applicable

. ( 11 .1) For aeroplanes in pre - mod 155648 and pre - SB A320 - 52 - 11 65 configuration : After optional modification as specified in paragraph ( 9 ) of this AD. ( 11 .2) For aeroplanes in post - mod 155648 or post - SB A320 - 52 - 11 65 configuration : From the effective date of this AD

.E ASA AD No.: 20 1 5 - 000 1 R1

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 5 / 5 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. Ref. Public ations: Airbus SB A320 - 52 - 1100 original issue dated 07 December 1998, or Revision 01 dated 12 March 1999. Airbus SB A320 - 52 - 1163 original issue dated 04 February 2014. Airbus SB A320 - 52 - 1165 original issue dated 03 November 2014. 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. Th e original issue of th is AD was posted on 17 December 2014 as PAD 14 - 176 for consultation until 01 January 2015. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E - mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements i n this AD, please contact: AIRBUS

– Airworthiness Office

– EIAS, Fax +33 5 61 93 44 51, E - mail: account.airworth - eas@airbus.com

.