EASA AD No.: 2009-0009

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0009 [Corrected 27 January 2009]

Date: 15 January 2009

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 participat e in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EC 1702/2003, Part 21A .3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Direc tive unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Regi stry [EC 216/2008, Article 14(4) exemption]. 

### Type Approval Holder’s Name :
CFM International SA Type/Model designation(s) :
CFM56-7B turbofan engines

TCDS Number : EASA.E.004

Foreign AD : Not applicable

Supersedure : None



### ATA 05 Time Limits – Low Pressure Turbine Rear Frame – Life Limit / Mandatory Inspection

Manufacturer(s): Snecma, GE Aviation

Applicability: CFM International CFM56-7B tu rbofan engines equipped with a low pressure turbine (LPT) rear frame part number (P/N) 340-166-254-0, 340-166-255-0, 340-166-256-0, 340-166-257-0, 34 0-166-258-0, 340-166-259-0, 340-177-551-0, 340-177-552-0, 34 0-177-553-0, 340-177-554-0, 340-177-555-0, 340-177-556-0. These engines are known to be installed on, but not limited to, Boeing 737series aeroplanes.

Reason: The concerned LPT rear frame part numbers were introduced by the CFM56-7B Service Bulletin S/B 72-0527 revision 02 issued 21 January 2008. They are obtained by modifying (reworking) older P/N. Before the issue of the CFM56-7B Engine Shop Manual (ESM) Temporary Revisions (TR) 05-0097, 05-0098, and 05-0099 on September 19, 2008, the concerned LPT rear frames were neither subject to a life limit nor to a mandatory inspection. This AD is issued to make sure that all operators are informed about the Low Cycle Fatigue (LCF) life limits or mandatory inspections affecting these new P/N and revise their aircraft maintenance programs accordingly. This AD has been corrected to amend a typographical error within the effective date and change this date from 28 January 2008 to 28 January 2009.EASA AD No.: 2009-0009

EASA Form 110 Page 2/3 Effective Date: 28 January 2009

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: 1) Within 30 days after the effective date of this AD, amend the approved operator maintenance programme to incorporate the new LCF life limits for LPT rear frame P/N 340-166-254-0, 340-166-255-0, 340-166-256-0, 340-166-257-0, 340-166-258-0, 340-166-259-0, 340-177-551-0, 340-177-552-0, 340-177-553-0, 340-177-554-0, 340-177-555-0, 340-177-556-0, in accordance with the CFM56-7B ESM chapter 05 Temporary Revision (TR) 05-0097, 05-0098, and 05-0099, as applicable or subsequent revisions of the Engine Shop Manual following Revision 38 that incorporate these Temporary Revisions. 2) If the number of total cycles accumulated by a LPT rear frame P/N 340-166-254-0, 340-166-255-0, 340-166-256-0, 340-166-257-0, 340-166-258-0, 340-166-259-0, 340-177-551-0, 340-177-552-0, 340-177-553-0, 340-177-554-0, 340-177-555-0, 340-177-556-0 cannot be positively established, then within 300 cycles after the effective date of the AD, remove and replace the LPT rear frame or perform the inspections in accordance with CFM56-7B Service Bulletin S/B 72-0558 revision 2, or CFM56-7B Service Bulletin S/B 72-0579 revision 4, as applicable.
Note: The number of total cycles accumulated of the LPT rear frame is the sum of the number of cycles accumulated before and after compliance with CFM56-7B S/B 72-0527.
Ref. Publications: CFM56-7B Engine Shop Manual chapter 05 Temporary Revisions (TR) 05-0097, 05-0098, and 05-0099, or subsequent revisions of the Engine Shop Manual following Revision 38 that incorporate these Temporary Revisions.
CFM56-7B Service Bulletin S/B 72-0558 revision 2
CFM56-7B Service Bulletin S/B 72-0579 revision 4 The use of later approved revisions of the Service Bulletins 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 November 2008 as PAD 08-130 for consultation until 24 December 2008. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu 4. For any question concerning the tec hnical content of the requirements in this AD, please contact: CFM SA Customer Support Center E-mail : snecma.csc@snecma.fr International Phone : +33 1 64 14 88 66 Fax : +33 1 64 79 85 55
or CFM Inc. Customer Support Center E-mail : geae.csc@ae.ge.com International Phone: +1 513-552-3272 USA Phone: 877-GEAE-CSCEASA AD No.: 2009-0009

EASA Form 110 Page 3/3