□FAA □Germany LBA ■EASA □CAA-NL □Brazil □UK CAA □Transport Canada Civil Aviation □Japan CAB □DGAC □CAA of Israel □Other ■是(Yes) □否(No) ＿ a.生效日期另訂為(Re-specify the effective date as)：＿＿＿＿＿＿＿＿＿＿＿＿＿＿＿＿ b.執行時限另訂為(Re-specify the compliance time or period as)：＿＿＿＿＿＿＿＿＿＿＿ 2.使用人是否需要將AD執行結果向民航局提出報告?(Do Users need to report the status of compliance to the CAA?) □是(Yes) ■否(No) CAA Form ACS-P08-02 第一頁/共一頁 註： 1. AD內容後附。 2. 航空器產品使用人得向民航局提出豁免、替代符合方法、執行時限之展延之申請。 3. 如有任何問題，請聯絡交通部民用航空局初始適航科。Tel：(02)2349-6331~3, Fax：(02)2545-8464, e-mail： [email protected]Note： 1. The AD text is enclosed. 2. Exemption, an alternative method of compliance or adjustment of the compliance time may be proposed to the CAA for approval. 3. For further information, please contact Civil Aeronautics Administration on Tel：(02)2349-6331~3, Fax：(02)2545-8464, e-mail：[email protected]設計國AD編號 Original AD number 2015-0133 1.直接採用原AD之內容?(Is the original AD directly adopted?) 備註 Note ATA 72. CFM International S.A. CFM56-7B SB 72-0964 (original not issued) Revision 1, dated December 15, 2014. and CFM International S.A. CFM56-7B S/B 72-0965, dated December 16, 2014. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD. CAA Original Authorities □本國產品 Native products □其他個案 Other 適用之航空產品 Applied to (models, serial numbers or part numbers, as applicable) CFM56-3, CFM56-3B and CFM56-3C engines, all serial numbers (s/n), and CFM56-7B engines, all certified models, all s/n, except models CFM56-7B27A, CFM56-7B27A/3 and CFM56-7B27AE. These engines are known to be installed on, but not limited to, Boeing 737-300, -400, -500, -600, -700, -800, -900 and - 900ER aeroplanes. 主旨摘要 Engine – Accessory Gearbox Gearshaft – Inspection / Replacement 民航局 設計國民航主關機構 收文者：中華航空股份有限公司 適航指令發布單 Airworthiness Directive Issuance Form 民航局AD編號 AD Number CAA-2015-07-004 發布日期 Date issued 2015/7/14 存檔序號:104-07-004 March 13.2009 Ver.3
Transcript
□FAA □Germany LBA
■EASA □CAA-NL
□Brazil □UK CAA
□Transport Canada Civil Aviation □Japan CAB
□DGAC □CAA of Israel
□Other
■是(Yes) □否(No) ＿
a.生效日期另訂為(Re-specify the effective
date as)：＿＿＿＿＿＿＿＿＿＿＿＿＿＿＿＿
b.執行時限另訂為(Re-specify the compliance
time or period as)：＿＿＿＿＿＿＿＿＿＿＿
2.使用人是否需要將AD執行結果向民航局提出報告?(Do
Users need to report the status of compliance to the CAA?)
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2015-0133 Date: 08 July 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 EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 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 [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].
Manufacturer(s): SNECMA and GE Aviation (formerly General Electric Aircraft Engines)
Applicability: CFM56-3, CFM56-3B and CFM56-3C engines, all serial numbers (s/n), and CFM56-7B engines, all certified models, all s/n, except models CFM56-7B27A, CFM56-7B27A/3 and CFM56-7B27AE.
These engines are known to be installed on, but not limited to, Boeing 737-300, -400, -500, -600, -700, -800, -900 and -900ER aeroplanes.
Reason: Reports have been received of uncommanded in-flight shutdowns on CFM56-7B engines, caused by premature wear of the 73-tooth gearshaft located in the engine accessory gearbox (AGB). CFM International has identified a batch of 73-tooth and 41-tooth gearshafts that show premature wear on the teeth, due to inadequate shot peening. The affected gearshafts exhibit micro-pitting which may lead to material separating from the gearshaft.
This condition, if not detected and corrected, could lead to failure of an AGB gearshaft, possibly resulting in engine failure or loss of thrust control, with consequent reduced control of the aeroplane.
Prompted by these findings, CFM published CFM56-7B Service Bulletin (SB) 72-0964 Revision 1 and SB 72-0965, providing instructions to inspect and replace the affected AGB gearshafts.
For the reasons described above, this AD requires repetitive magnetic chip detector (MCD) inspections of the affected AGB gearshafts and their eventual removal from service. As the affected parts are also eligible for installation on CFM56-3 engines and some spares are affected, this AD also applies to those engines.
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously:
Note: For the purpose of this AD, an affected 41-tooth or 73-tooth AGB gearshaft is one identified by Part Number (P/N) and s/n in Appendix 1 or Appendix 2, as applicable, of this AD, which also identify the engine s/n (ESN) of the CFM56-7B engines on which the affected parts were known to be installed.
For CFM56-7B engines :
(1) Within 25 flight hours (FH) after the effective date of this AD, determine whether an affected 41-tooth AGB gearshaft P/N 335-303-002-0 (intermediate line 7) or 73-tooth AGB gearshaft P/N 335-302-902-0 (fuel pump line 6) is installed on the engine. A review of engine maintenance records is acceptable to make this determination, provided the P/N and s/n of the installed AGB gearshaft can be conclusively identified from that review.
(2) For an engine with an affected AGB gearshaft installed, as determined by paragraph (1) of this AD, initially within the compliance time specified in Table 1 of this AD, as applicable, and, thereafter, at intervals not to exceed 500 FH, accomplish an AGB/TGB (transfer gearbox) MCD inspection in accordance with the instructions of CFM56-7B SB 72-0964.
Table 1 – Inspection Threshold
Gearshaft Compliance Time (A, B, or C, whichever occurs later)
73-tooth
A: Within 250 FH since last AGB/TGB MCD inspection
B: Within 25 FH after the effective date of this AD
C: Before the gearshaft exceeds 3 000 FH since first installation on an engine
41-tooth
A: Within 250 FH since last AGB/TGB MCD
B: Within 25 FH after the effective date of this AD
C: Before the gearshaft exceeds 6 000 FH since first installation on an engine
(3) If, during any AGB/TGB MCD inspection as required by paragraph (2) of this AD, any magnetic particles, including fuzz, are seen, accomplish a particles laboratory analysis, and, if the particles are 73-tooth or 41-tooth gearshaft material, as applicable, within 75 FH since the AGB/TGB MCD inspection, remove the affected AGB gearshaft(s) from service.
(4) Terminating Action
(4.1) Before exceeding 6 000 FH since first installation on an engine, or within 50 FH after the effective date of this AD, whichever occurs later, remove each affected 73-tooth AGB gearshaft from service.
(4.2) Before exceeding 9 000 FH since first installation on an engine, or within 50 FH after the effective date of this AD, whichever occurs later, remove each affected 41-tooth AGB gearshaft from service.
The actions required by this paragraph can be accomplished in accordance with the instructions of CFM56-7B SB 72-0965.
For all engines :
(5) From the effective date of this AD, it is allowed to install on any engine a 41-tooth AGB gearshaft P/N 335-303-002-0 (intermediate line 7) or 73-tooth AGB gearshaft P/N 335-302-902-0 (fuel pump line 6), provided that, prior to installation, it is determined that this is not an affected AGB gearshaft as identified in Appendix 1 or Appendix 2 of this AD.
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Ref. Publications: CFM International S.A. CFM56-7B SB 72-0964 (original not issued) Revision 1, dated December 15, 2014.
CFM International S.A. CFM56-7B S/B 72-0965, dated December 16, 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 22 May 2015 as PAD 15-066 for consultation until 30 June 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: [email protected].
4. For any question concerning the technical content of the requirements in this AD, please contact:
CFM SA Customer Support Center E-mail : [email protected]. International Telephone : +33 1 6414 8866, Fax : +33 1 6479 8555,
or
CFM Inc. Customer Support Center E-mail : [email protected]. International Telephone: +1 513 552 3272, Fax : +1 513 552 3329.
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