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EASA AD No.: 2014-0014 EASA AIRWORTHINESS DIRECTIVE AD No.: 2014-0014 Date: 14 January 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 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]. Design Approval Holder s Name: AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes TCDS Number: EASA.A.064 Foreign AD: Supersedure: Not applicable This AD supersedes DGAC France AD 2001-062 dated 21 February 2001, and EASA AD 2010-0091R1 dated 12 October 2010. ATA 55 Stabilizers Elevators Inspection Manufacturer(s): Applicability: Airbus (formerly Airbus Industrie) 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 number. Reason: Trapped liquid was reported in the honeycomb core of pre-mod 23558 elevators installed on A320 family aeroplanes. This condition, if not detected and corrected, could lead to disbonding between the affected elevator panel skin and honeycomb core, affecting the structural integrity of the elevator structure. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-55-1024, providing instructions to accomplish a one-time inspection and, depending on findings, repair, modification and re-protection of the affected elevators. Consequently, DGAC France issued AD 2001-062 to require the actions specified in that SB. Since that AD was issued, a special detailed repetitive inspection applicable to all pre-mod 35515 elevators was introduced with ALI task 552007 in ALS Part 2 under ALI Document reference AI/SE-M4/95A.0252/96 at issue 7, approved by EASA on 07 February 2006 and mandated by EASA AD 2006-0165. EASA AD 2006-0165 was superseded by EASA AD 2010-0071R1, which required implementation of the actions contained in issue 10 of the ALI TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 1/5

document. Effective Date: 28 January 2014 EASA AD No.: 2014-0014 As a consequence of the increasing number of elevators being inspected, it was reported that some elevators may have been moved from the aeroplane on which they were originally fitted to another aeroplane, and spare parts may have been installed without having been inspected within the applicable required time frame as per ALI task 552007 requirements. Consequently, EASA issued AD 2010-0091 (later revised) to require identification and inspection of elevators installed on aeroplanes that had not been inspected within the applicable time frame as per ALI task 552007. Since those ADs were issued, Airbus decided to replace the ALI Task 552007 with an inspection SB, in which threshold, interval, inspection method, and applicable corrective actions remain unchanged. For the reason described above, this AD supersedes DGAC France AD 2001-062 and EASA AD 2010-0091R1 and requires repetitive inspections to detect liquid ingress potentially trapped into the elevator structure and, depending on findings, accomplishment of applicable corrective actions. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 3 months after the effective date of this AD, identify the Part Number (P/N) and serial number (s/n) of the left-hand (LH) and right-hand (RH) elevator on the aeroplane to determine whether the P/N is listed in Appendix 1 of this AD. A review of the aeroplane delivery or maintenance records is acceptable for the P/N determination requirements of paragraph (1) of this AD, provided that the aeroplane configuration and installed components can be conclusively determined from that review. (2) Based on the determination as required by paragraph (1) of this AD, for aeroplanes with an elevator installed, as identified in Appendix 1 of this AD, within the threshold defined in Table 1 of this AD, and, thereafter, at intervals not to exceed 6 years since first flight after last inspection and/or repair, accomplish a thermographic inspection of the affected elevator top and bottom skin panels in accordance with the instructions of Airbus SB A320-55-1046. Table 1 Aeroplane configuration Having an elevator installed with a P/N and s/n as specified in Appendix 1 of this AD, Table 1 or Table 2 Having an elevator installed with a P/N and s/n as specified in Appendix 1 of this AD, Table 3 or Table 4 Compliance time (whichever occurs later) Within 6 years since first flight of the elevator, or since first flight of the elevator after Airbus SB A320-55-1024 embodiment, or since first flight after last ALI 552007 inspection, as applicable Within 12 years since the elevator first flight, or within 6 years since first flight of the elevator after last ALI 552007 inspection, as applicable (3) If, during any inspection as required by paragraph (2) of this AD, water ingress is confirmed, before next flight, accomplish the applicable corrective actions in accordance with the instructions of Airbus SB A320-55-1046. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 2/5

EASA AD No.: 2014-0014 Note 1: Accomplishment of the instructions of Airbus SB A320-55-1046 is a substitute for the actions specified in ALI task 552007. (4) Installation on an aeroplane of elevators having a P/N not listed in Appendix 1 of this AD (post-mod 35515) constitutes terminating action for the repetitive inspections required by this AD for that aeroplane. (5) Aeroplanes on which Airbus Modification (Mod.) 35515 has been embodied in production are not affected by the inspection requirements of this AD, provided that, since aeroplane first flight, no elevator has been installed having a P/N and s/n as listed in Appendix 1 of this AD. (6) From the effective date of this AD, it is allowed to install an elevator having a P/N and s/n as listed in Appendix 1 of this AD, on an aeroplane, provided that, following installation, that elevator is inspected and, depending on findings, corrected as required by this AD. Note 2: It is the responsibility of the operator to ensure that the applicable compliance limit is transferred with the elevator to the aeroplane on which the elevator is (to be) installed. (7) From the effective date of this AD, do not operate an aeroplane with an elevator installed having a P/N and s/n as listed in Appendix 1 of this AD, Table 1 or Table 2, unless that elevator has already been inspected and re-protected (as previously required by DGAC France AD 2001-062) in accordance with the instructions of Airbus SB A320-55-1024. Ref. Publications: Airbus SB A320-55-1024 original issue dated 13 January 1999, or Revision 01 dated 04 November 2003. Airbus SB A320-55-1046 original Issue dated 28 February 2013, or Revision 01 dated 09 October 2013. 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. This AD was posted on 13 November 2013 as PAD 13-167 for consultation until 11 December 2013. 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, Executive 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 - EIAS, Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 3/5

EASA AD No.: 2014-0014 Appendix 1 Affected Elevators, LH and RH Note: Airbus SB A320-55-1042 (mod 150390) includes the installation of an additional marking plate on the elevator front spar and re-identification of the elevator surface depending on its weight and production P/N. As a pre-requisite to SB A320-55-1042 accomplishment, the affected elevator should have been weighed in accordance with Component Maintenance Manual (CMM) 55-21-15, or SB A320-55-1034 instructions. Table 1 Pre-mod 23558 elevators, not having embodied Airbus SB A320-55-1042 (Airbus mod 150390) Part name P/N (first 12 digits only) s/n LH Elevator RH Elevator D55280001000 D55280001001 1002 to 1472 inclusive, 1491 and FIC1 Table 2 Pre-mod 23558 elevators, having embodied Airbus SB A320-55-1042 (Airbus mod 150390) Part name P/N (first 12 digits only) s/n LH Elevator RH Elevator D55280003000 D55280003002 D55280003004 D55280003001 D55280003003 D55280003005 1002 to 1472 inclusive, 1491 and FIC1 Table 3 Post-mod 23558 and pre-mod 35515 elevators, not having embodied Airbus SB A320-55-1042 (Airbus mod 150390) Part name P/N (first 12 digits only) s/n LH Elevator RH Elevator D55280001000 D55280001002 D55280001004 D55280001008 D55280001010 D55280001012 D55280001001 D55280001003 D55280001005 D55280001009 D55280001011 D55280001013 All, except 1002 to 1472 inclusive, 1491 and FIC1 All All, except 1002 to 1472 inclusive, 1491 and FIC1 All TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 4/5

EASA AD No.: 2014-0014 Table 4 Post-mod 23558 and pre-mod 35515 elevators, having embodied Airbus SB A320-55-1042 (Airbus mod 150390) Part name P/N (first 12 digits only) s/n LH Elevator RH Elevator D55280003000 D55280003002 D55280003004 D55280003006 D55280003008 D55280003010 D55280003012 D55280003014 D55280003016 D55280003018 D55280003020 D55280003022 D55280003024 D55280003026 D55280003028 D55280003030 D55280003032 D55280003034 D55280003001 D55280003003 D55280003005 D55280003007 D55280003009 D55280003011 D55280003013 D55280003015 D55280003017 D55280003019 D55280003021 D55280003023 D55280003025 D55280003027 D55280003029 D55280003031 D55280003033 D55280003035 All, except 1002 to 1472 inclusive, 1491 and FIC1 All All, except 1002 to 1472 inclusive, 1491 and FIC1 All TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 5/5

EASA AD No.: 2014-0058 EASA AIRWORTHINESS DIRECTIVE AD No.: 2014-0058 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 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]. Design Approval Holder s Name: AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes TCDS Number: Foreign AD: Supersedure: EASA.A.064 Not Applicable None ATA 32 Landing Gear Main Landing Gear Sliding Tube Axles Inspection Manufacturer(s): Applicability: Reason: Airbus (formerly Airbus Industrie) 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 (MSN). A main landing gear (MLG) sliding tube axle rupture occurred in service. Investigation of the affected part showed 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 was subsequently identified whose axles may have been subject to this grinding operation, 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 failure 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 described above, this AD requires a one-time Special Detailed Inspection (SDI) of the axle on the affected MLG sliding tubes and, depending on findings, replacement of the MLG sliding tube. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 1/5

EASA AD No.: 2014-0058 Effective Date: 25 March 2014 Required Action(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) Identify 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. An aeroplane with an MSN not listed in Table 1 of this AD is not affected by the requirements of paragraphs (1.2) and (2) of 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 has been installed on that aeroplane since first entry into service. (1.2) For each 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 AD 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: After 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. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 2/5

EASA AD No.: 2014-0058 Ref. Publications: 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 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. 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 to the Safety Information Section, Executive 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 EIAS, Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 3/5

EASA AD No.: 2014-0096 EASA AIRWORTHINESS DIRECTIVE AD No.: 2014-0096 Date: 23 April 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 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]. Design 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 52 Doors Main Landing Gear Fixed Fairing Assembly Inspection Manufacturer(s): Applicability: Reason: Airbus (formerly Airbus Industrie) 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. Several occurrences of in-flight loss of main landing gear (MLG) fixed and hinged 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 maintenance documents were corrected to prevent miss-rigging of the MLG fixed and hinged fairings, which could induce fatigue cracking. In 1997, Airbus issued Service Bulletin (SB) A320-52-1083, providing instructions for a one-time inspection of the MLG fixed fairing composite insert and the surrounding area, replacement of the adjustment studs at the lower forward position and adjustment to the new clearance tolerances. In 1998, Airbus SB A320-52-1083 was superseded by Airbus SB A320-52-1100 (modification 27716) introducing a re-designed location stud, rod end and location plate at the forward upper and lower leg fixed-fairing positions. In 2012, reports were received of post-mod 27716 / post-sb A320-52-1100 MLG fixed fairing assemblies with corrosion, which could also induce cracking. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 1/3

EASA AD No.: 2014-0096 Effective Date: 07 May 2014 This condition, if not detected and corrected, could lead to further cases of inflight detachment of a MLG fixed fairing, possibly resulting in injury to persons on the ground and/or damage to the aeroplane. For the reason described above, this AD requires repetitive detailed inspections (DET) of the MLG fixed fairings, and, depending on findings, accomplishment of applicable corrective actions. This AD also prohibits installation of certain MLG fixed fairing rod end assemblies and studs (see Table 1 of this AD) as replacement parts on aeroplanes which have embodied Airbus mod 27716 in production, or have been modified in accordance with Airbus SB A320-52-1100 (any revision) in service. This AD is considered an interim action, pending introduction of a terminating modification, and further AD action may follow. 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 Part Number (P/N) in Table 1 of this AD, within the compliance time as specified in Table 2 of this AD, and, thereafter, at intervals not exceeding 6 500 flight cycles (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 Pre-mod 27716 (pre-sb A320-52-1100) Components Part Name Plate - Support Stud - Adjustment Rod end assembly (lower) Rod end assembly (upper) Part Number D5284024820200 D5284024420000 D5284000500000 D5284000600000 Table 2 Initial Inspection for Pre-mod 27716 Aeroplanes Compliance time (whichever occurs later, A, B, C or D) A B C D Before exceeding 6 500 FC since aeroplane first flight Within 6 500 FC since last installation of the pre-mod 27716 stud on an aeroplane Within 1 500 FC after the effective date of this AD Within 8 months after the effective date of this AD (2) For aeroplanes in post-mod 27716 (or post-airbus SB A320-52-1100) configuration, within the compliance time as specified in Table 3 of this AD, and, thereafter, at intervals not exceeding 12 months (except as specified below), accomplish a DET of each forward stud assembly, both RH and LH MLG, in accordance with the instructions of Airbus SB A320-52-1163. When, following any DET as required by this paragraph, both RH and LH MLG forward stud assemblies on an aeroplane are replaced with new ones, the next DET for that aeroplane can be deferred up to 72 months after replacement. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 2/3

EASA AD No.: 2014-0096 Table 3 Initial Inspection for Post-mod 27716 Aeroplanes Compliance time (whichever occurs later, A, B, C or D) A B C D Before exceeding 72 months since aeroplane first flight Within 72 months since last installation of the stud post-mod 27716 or since Airbus SB A320-52-1100 accomplishment Within 1 500 FC after the effective date of this AD Within 8 months after the effective date of this AD (3) If, during any DET as required by paragraph (2) of this AD, any crack, damage or corrosion 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. (4) Replacement of parts on an aeroplane as required by paragraph (1) or (3) of this AD, as applicable, does not constitute terminating action for the repetitive DET required by this AD for that aeroplane. (5) 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 paragraph (2) of this AD to determine the next due DET after modification and the applicable repetitive DET interval. (6) Do not install on any aeroplane a component as listed in Table 1 of this AD, as required by paragraph (6.1) or (6.2) of this AD, as applicable: (6.1) For aeroplanes in pre-mod 27716 and pre-airbus SB A320-52-1100 configuration: After optional modification as specified in paragraph (4) of this AD. (6.2) For aeroplanes in post-mod 27716 or post-airbus SB A320-52-1100 configuration: From the effective date of this AD. Ref. Publications: 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. 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. This AD was posted on 10 March 2014 as PAD 14-049 for consultation until 07 April 2014. 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, Executive 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 EIAS, Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 3/3

EASA AD No.: 2014-0130 EASA AIRWORTHINESS DIRECTIVE AD No.: 2014-0130 Date: 20 May 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 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]. Design Approval Holder s Name: CFM INTERNATIONAL S.A. Type/Model designation(s): CFM56-5B and CFM56-7B engines TCDS Number: Foreign AD: Supersedure: EASA.E.003, EASA.E.004 Not applicable None ATA 05 Time Limits Engine Stationary Parts Life Limits / Mandatory Inspections Manufacturer(s): Applicability: Reason: SNECMA, General Electric CFM56-5B engines, all models, all serial numbers. CFM56-7B engines, all models, all serial numbers. These engines are known to be installed on, but not limited to, Airbus A318, A319, A320 and A321 aeroplanes; and Boeing 737-600, -700, -800, -900 and -900ER aeroplanes. Stationary components were identified by CFM International S.A. (CFM) as life limited in service. Neither CFM56-5B Engine Shop Manual (ESM) nor CFM56-7B ESM contained instructions for calculation of remaining cyclic life for life limited engine stationary parts which were previously operated on a different engine type or model (configuration). This condition, if not corrected, could lead to operation of an engine stationary part beyond its technical life limit and consequent engine structural failure, possibly resulting in damage to the aeroplane and/or injury to the occupants. To address this potentially unsafe condition, CFM issued CFM56-5B ESM Temporary Revision (TR) 05-0223 and CFM-7B ESM TR 05-0163 to provide a method to determine the remaining life of each affected engine stationary part. For the reasons described above, this AD requires calculation of the remaining life of each affected engine stationary part and, depending on the calculation results, replacement or inspection of each part, as applicable. Effective Date: 03 June 2014 TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 1/2

EASA AD No.: 2014-0130 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 12 months after the effective date of this AD, identify each life limited stationary part installed on an engine which was previously operated in different engine model configuration. A review of engine maintenance records is acceptable to make these identifications, provided that the operational history of each life limited engine stationary part can be conclusively determined from that review. (2) If, during the identification as required by paragraph (1) of this AD, an engine stationary part is identified that has previously been operated in a different engine type or different engine model (including different configuration, thrust rating), within 12 months after the effective day of this AD, calculate the remaining life of each engine stationary part in accordance with the instructions of CFM56-5B ESM page block 05-12-00, as amended in accordance with TR 05-0223, or CFM56-7B ESM page block 05-12-00, as amended in accordance with TR 05-0163, as applicable to engine type. (3) Depending on the result of the calculation as required by paragraph (2) of this AD, within 50 engine cycles, or before exceeding the calculated remaining life, whichever occurs later after calculation as required by paragraph (2) of this AD, replace each affected part with a serviceable part, or inspect each part (including all applicable corrective actions, depending on findings) in accordance with the approved maintenance instructions, as applicable. (4) From the effective date of this AD, installation on an engine of a used life limited engine stationary part that has previously been operated in a different engine type or different engine model (including different configuration, thrust rating) is allowed, provided that, prior to installation, the applicable remaining life of the engine stationary part is calculated as specified in paragraph (2) of this AD and, thereafter, each affected part is inspected or replaced, as applicable, before exceeding the calculated remaining life. Ref. Publications: CFM56-5B ESM, as amended by TR 05-0223 dated 29 August 2013, CFM56-7B ESM, as amended by TR 05-0163 dated 29 August 2013. 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. This AD was posted on 12 February 2014 as PAD 14-036 for consultation until 12 March 2014. 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, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu. 4. For any question concerning the technical content of the requirements in this AD, please contact: CFM SA Customer Support Center E-mail : snecma.csc@snecma.fr. International Phone : +33 1 6414 8866 Fax : +33 1 6479 8555, or CFM Inc. Customer Support Center E-mail : geae.aoc@ge.com. International Phone: +1 513 552 3272 Fax : +1 513 552 3329. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 2/2

EASA AD No.: 2014-0141 EASA AIRWORTHINESS DIRECTIVE AD No.: 2014-0141 Date: 04 June 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 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]. Design Approval Holder s Name: AIRBUS Type/Model designation(s): A318, A319 and A320 aeroplanes TCDS Number: Foreign AD: Supersedure: EASA.A.064 Not applicable None ATA 32 Landing Gear Main Landing Gear Upper Cardan Life Limitation Manufacturer: Applicability: Reason: Airbus (formerly Airbus Industrie) 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 and A320-233 aeroplanes, all manufacturer serial numbers. During an A320-200 77T main landing gear (MLG) fatigue test by Messier Bugatti-Dowty (MBD), an upper cardan was found with a crack, emanating from the grease hole / main lug intersection. The affected upper cardan, Part Number (P/N) 201163620, is listed in the applicable Airworthiness Limitations Section (ALS) Part 1 with a demonstrated fatigue life of 60 000 landings. This condition, if not corrected, could lead to MLG upper cardan failure, possibly resulting in MLG collapse and subsequent damage to the aeroplane and injury to occupants. Prompted by these findings and further to analysis, it has been decided to reduce the life limit for certain installations of the P/N 201163620 MLG upper cardan. For the reasons described above, this AD requires implementation of the new life limits, as applicable, and replacement of any affected MLG upper cardan units that have already exceeded the reduced limit. The reduced life limits for the affected MLG upper cardan are expected to be incorporated in a next revision of the Airbus A318/A319/A320/A321 ALS Part 1. Effective Date: 18 June 2014 TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 1/3

EASA AD No.: 2014-0141 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 3 months after the effective date of this AD, or before exceeding the life limit as defined in Appendix 1 of this AD, as applicable, whichever occurs later, replace each MLG upper cardan P/N 201163620 with a serviceable part. Note 1: For the purpose of this AD, a serviceable MLG upper cardan is a part having P/N 201163620 that has not exceeded the life limit defined in Appendix 1 of this AD, or a MLG upper cardan having a different P/N that has not exceeded the life limit defined in Airbus A318/A319/A320/A321 ALS Part 1 Revision 02. (2) From the effective date of this AD, it is allowed to install a MLG upper cardan P/N 201163620 on an aeroplane, provided the part life has not exceeded the life limit defined in Appendix 1 of this AD, as applicable, and that, following installation, it is replaced before exceeding the applicable life limit as defined in Appendix 1 of this AD (see Notes 4 and 6) with a serviceable part (see Note 1 above). Ref. Publications: Airbus A318/A319/A320/A321 ALS Part 1 Revision 02, dated 13 May 2011. The use of later approved revisions of this document 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 25 March 2014 as PAD 14-057 for consultation until 08 April 2014. 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, Executive 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 EIAS, Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 2/3

Appendix 1 MLG Upper Cardan P/N 201163620 Life Limit EASA AD No.: 2014-0141 Note 2: Note 3: Note 4: Note 5: Note 6: Note 7: The life limit as specified in this Appendix (see table below) is counted in landings, accumulated by the MLG unit since its first installation on an aeroplane. The life limit applies only where the installation is valid for the given aeroplane model, configuration, and weight variant (WV). In case of transfer of a part between aeroplanes having a different life limitation, refer to the Airbus A318/A319/A320/A321 ALS Part 1 Revision 02 sub-part 1-0 paragraph 6 for the method to adjust the life limitation. A MLG unit on which Airbus modification (mod) 26644 is embodied (i.e. post-mod) is also known as Enhanced landing gear. Pre-mod 26644 MLG units are identified as P/N 201375xxx Leg and Dressing Series and post-mod 26644 MLG units are identified as P/N 201582xxx Leg and Dressing series. For aeroplanes and configurations not defined in the table below, the life limitation is unchanged and those as specified in Airbus A318/A319/A320/A321 ALS Part 1 at Revision 02 still apply. Certain life limits were stated incorrectly in PAD 14-057, as 50 950 FC instead of 50 590 FC. The Table below shows the correct values. Affected aeroplanes Life Limit (see Note 2 above) A319 pre-mod 26644, excluding Corporate Jets post-mod 28238, 28162 and 28342 50 590 A319 post-mod 26644, excluding Corporate Jets post-mod 28238, 28162 and 28342 56 480 A320 Twin pre-mod 26644, WV012, WV011, WV016 and WV018 50 590 A320 Twin post-mod 26644, WV012, WV011, WV016 and WV018 56 480 A320 Twin post-mod 26644, WV015 and WV017 42 140 TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 3/3

EASA AD No.: 2014-0147 EASA AIRWORTHINESS DIRECTIVE AD No.: 2014-0147 Date: 11 June 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 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]. Design Approval Holder s Name: AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes TCDS Number: Foreign AD: EASA.A.064 Not applicable Supersedure: This AD supersedes EASA AD 2008-0150 dated 05 August 2008. ATA 27 Flights Controls Trimmable Horizontal Stabilizer Actuator Inspection Manufacturer(s): Applicability: Reason: Airbus (formerly Airbus Industrie) 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. The Trimmable Horizontal Stabilizer Actuator (THSA) of Airbus A320 Family aeroplanes has been rig-tested to check its behaviour in case of primary load path failure. In that configuration, the loads are transferred to the secondary nut, which should jam, preventing any THS motion. The test results showed that the secondary nut did not jam as expected, preventing detection of the primary load path failure. In order to verify the integrity of the THSA primary load path, EASA issued AD 2006-0223 to require two different repetitive inspections on the Lower and Upper THSA attachments to obtain confirmation that the secondary load path is not loaded. While performing these repetitive inspections, several occurrences of an incorrect THSA installation have been found. This condition, if not detected and corrected, could lead to a degradation of the integrity of the THSA primary load path and to secondary load path partial or full engagement. To address these findings, EASA issued AD 2007-0178 to require a one-time detailed visual inspection of specific parts of the THSA attachments. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 1/3

EASA AD No.: 2014-0147 Effective Date: 25 June 2014 Subsequently, EASA issued AD 2008-0150, retaining the requirements of AD 2006-0223 and AD 2007-0178, which were superseded, and in addition required repetitive detailed visual inspections of specific parts of the THSA attachments. Since EASA AD 2008-0150 was issued, Airbus issued Service Bulletin (SB) A320-27-1164 Revision 10 to provide instructions for additional general visual inspections of the THSA ballscrew thread to detect dents. For the reason described above, this EASA AD retains the requirements of EASA AD 2008-0150, which is superseded, and requires supplementary repetitive inspections of the THSA ball screw to detect dents and, depending on findings, accomplishment of applicable corrective action(s). Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 20 months since aeroplane first flight, or within 20 months since the last inspection of the lower THSA attachment in accordance with the instructions of Airbus SB A320-27-1164 (Revision 02 up to Revision 09), whichever occurs later, and, thereafter, at intervals not exceeding 20 months, accomplish the following actions concurrently, as specified in paragraphs (1.1), (1.2), (1.3) and (1.4) in accordance with the instructions of Airbus SB A320-27-1164 Revision 10. (1.1) Check the clearance between the secondary nut trunnions and the junction plates at the lower THSA attachment. (1.2) Visually inspect the lower THSA attachment for correct installation of attachment parts. (1.3) Visually inspect the ball screw. (1.4) Depending on findings during the actions as required by paragraph (1.1), or (1.2), or (1.3) of this AD, accomplish the applicable corrective actions. (2) Within 10 months since aeroplane first flight, or within 10 months since the last inspection of the upper THSA attachment in accordance with the instructions of Airbus SB A320-27-1164 (Revision 02 up to Revision 09), whichever occurs later, and, thereafter, at intervals not exceeding 10 months, accomplish the following actions concurrently, as specified in paragraphs (2.1), (2.2) and (2.3) in accordance with the instructions of Airbus SB A320-27-1164 Revision 10. (2.1) Inspect the upper THSA attachment for correct installation, cracks, damage, and metallic particles. (2.2) Visually inspect the upper attachment for correct installation of attachment parts. (2.3) Depending on findings during the inspections as required by paragraph (2.1) or (2.2) of this AD, accomplish the applicable corrective actions. (3) Within 30 days after each action as required by paragraphs (1) and (2) of this AD, in case of any findings, report to AIRBUS, using the Appendix 01 Inspection Reporting Sheet of SB A320-27-1164 Revision 10. (4) Corrective actions, as required by paragraph (1.4) or (2.3) of this AD, as applicable, do not constitute terminating action for the repetitive check/inspection requirements of paragraphs (1) and (2) of this AD. Ref. Publications: Airbus SB A320-27-1164 Revision 02 dated 30 March 2005, or Revision 03 dated 24 August 2005, or Revision 04 dated 17 July 2006, or Revision 05 dated 11 January 2007, or Revision 06 dated 01 April 2008, or Revision 07 TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 2/3

EASA AD No.: 2014-0147 dated 23 June 2009, or Revision 08 dated 06 July 2010, or Revision 09 dated 02 May 2012, or Revision 10 dated 27 March 2014. The use of later approved revisions of this document 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 28 April 2014 as PAD 14-076 for consultation until 26 May 2014. 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, Executive 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 EIAS; Fax +33 5 61 93 44 51; E-mail: account.airworth-eas@airbus.com. TE.CAP.00110-003 European Aviation Safety Agency. All rights reserved. 3/3