国空機第1559号 整理番号 TCD-7683A-2014
耐 空 性 改 善 通 報
平成26年4月9日
適用航空機の所有者各位
国土交通省航空局長 田村 明比古
1. 第2項の航空機又はその装備品等の安全性又は環境適合性を確保するため、第3項の整備又は改造作業等の実施が必要であると認められますので通報します。
なお、本通報による検査、修理、交換、改造等が実施されないときは、航空法第14条の2第1項に基づく整備改造命令を発出し、又は同法第134条第2項に規定された立入検査を実施のうえ、同法第14条の2第2項の規定により耐空証明の効力を停止し、若しくは有効期間を短縮し、又は同法第10条第3項（同法第10条の2第2項において準用する場合を含む。）の規定により指定した事項を変更する場合があります。
また、本通報により実施した作業については、同法第58条第2項に定めるとおり航空日誌に記載することが求められます。
2. 適用航空機
エアバス（エアバス・インダストリー）式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及びA321-232 型
3. 適用項目
昇降舵のハニカム・コアに液体が溜まることにより、外板とハニカム・コアが剥離し、昇降舵構造の健全性の低下に至る不具合を防止するため、既に実施した場合を除き、別添EASA AD 2014-0014（以下「AD」という。）のRequired Action(s) and Compliance Time(s)項に従って、繰り返し検査及び必要に応じ処置を実施すること。
ただし、AD中「the effective date of this AD」とあるのは「本通報発効日」（第4.1項による。）と、「DGAC France AD 2001-062」とあるのは「耐空性改善通報TCD-5573-2001」と、それぞれ読み替えるものとする。
なお、本通報による処置を他の同等な方法で実施する場合には、航空局長の承認が必要である。ただし、ADに係る同等な方法としてEASAの承認を受けているSB等に従って処置を実施する場合（運用限界の変更を伴う場合を除く。）には、航空局長への届出でよい。
4. 備考
4.1 本通報は、平成26年4月10日から発効する。
4.2 本通報により、耐空性改善通報TCD-5573-2001（平成13年4月23日発効）、耐空性改善通報TCD-7683-2010（平成22年9月15日発効）及び耐空性改善通報TCD-7683-1-2010（平成22年10月28日発効）を廃止する。
4.3 本通報は、EASA AD 2014-0014による。
4.4 本通報の送付を受けた者は、参考配布を除き、平成26年4月21日までに、適用項目に関する実施状況を記載した報告書を、地方航空局先任航空機検査官又は空港事務所駐在航空機検査長に提出すること。記載要領、様式及び提出先については、航空機検査業務サーキュラーNo.3-003に従うこと。
4.5 エアバス・サービス・ブレティンA320-55-1024（1999年1月13日付け）及び同Revision 01（2003年11月4日付け）、エアバス・サービス・ブレティンA320-55-1046（2013年2月28日付け）及び同Revision 01（2013年10月9日付け）並びに承認されたこれらのその後の改訂版は本件に関するものである。
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: Not applicable
Supersedure: 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):
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 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 document.
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.
Effective Date:
28 January 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, 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
Compliance time (whichever occurs later)
Having an elevator installed with a P/N and s/n as specified in Appendix 1 of this AD, Table 1 or Table 2
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
Having an elevator installed with a P/N and s/n as specified in Appendix 1 of this AD, Table 3 or Table 4
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.
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.
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
D55280001000
1002 to 1472 inclusive, 1491 and FIC1
RH Elevator
D55280001001
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
D55280003000
D55280003002
D55280003004
1002 to 1472 inclusive, 1491 and FIC1
RH Elevator
D55280003001
D55280003003
D55280003005
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
D55280001000
All, except 1002 to 1472 inclusive, 1491 and FIC1
D55280001002
D55280001004
D55280001008
D55280001010
D55280001012
All
RH Elevator
D55280001001
All, except 1002 to 1472 inclusive, 1491 and FIC1
D55280001003
D55280001005
D55280001009
D55280001011
D55280001013
All
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
D55280003000
D55280003002
D55280003004
All, except 1002 to 1472 inclusive, 1491 and FIC1
D55280003006
D55280003008
D55280003010
D55280003012
D55280003014
D55280003016
D55280003018
D55280003020
D55280003022
D55280003024
D55280003026
D55280003028
D55280003030
D55280003032
D55280003034
All
RH Elevator
D55280003001
D55280003003
D55280003005
All, except 1002 to 1472 inclusive, 1491 and FIC1
D55280003007
D55280003009
D55280003011
D55280003013
D55280003015
D55280003017
D55280003019
D55280003021
D55280003023
D55280003025
D55280003027
D55280003029
D55280003031
D55280003033
D55280003035
All |