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 participate 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 accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directive 

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]. 

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 turbofan 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, 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. 

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 & Research Section, Certification 

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 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-CSC 
EASA AD No.: 2009-0009 

EASA Form 110 Page 3/3