1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2007-0221 

Date: 13 August 2007

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry. 

Type Approval Holder: 

CFM International SA (CFM) 

Type/Model Designation(s): 

CFM56-5B series engines 

TC/TCDS Number: EASA E.003 

Foreign AD: Not applicable 

Supersedure: None 

ATA 05 Time Limits – Low Pressure Turbine Rear Frame – Life Reduction 

Manufacturer(s): Snecma, General Electric 

Applicability: CFM International (CFM) Model CFM56-5B1/P, -5B2/P, -5B3/P, -5B3/P1, 

-5B4/P, -5B4/P1, -5B5/P, -5B6/P, -5B7/P, -5B8/P and -5B9/P turbofan engines 

operating in commercial application and Model CFM56-5B6/P and -5B7/P 

turbofan engines operating in corporate application (conversion per SB 72-

0308), if equipped with a low pressure turbine (LPT) rear frame part number 

(P/N) 338-171-703-0, 338-171-704-0, 338-171-705-0 or 338-171-706-0. 

These engines are known to be installed on, but not limited to, Airbus A318, 

A319, A320 and A321 series aircraft. 

Reason: Before the issue of the CFM56-5B Engine Shop Manual (ESM) Temporary 

Revision (TR) 05-0145, the concerned LPT rear frames were not subject to a 

life limit in commercial applications, and in corporate applications the CFM56-

5B6/P and –5B7/P engines were life limited to 22 500 cycles.

Using a refined damage tolerant approach accounting for crack initiation and 

propagation to ensure any cracking that is present will not grow to unsafe 

levels, CFM has now established a low cycle fatigue (LCF) life limit for the 

concerned LPT rear frames. This requirement was first introduced by revision 

TR 05-0145 of the CFM56-5B ESM. This revision is approved by EASA and its 

content has been integrated in revision 47 of the CFM56-5B ESM, dated 

January 15, 2007. 

For the reason described above, this AD requires operators to revise their 

aircraft maintenance programs in accordance with these LCF life limits affecting 

new P/Ns. 

Effective Date: 27 August 2007 
2/2 

Compliance: (1) For LPT rear frame P/N 338-171-703-0, 338-171-704-0, 338-171-705-0, 

338-171-706-0, comply with the LCF life limits in accordance with the 

chapters 05-12-04, 05-12-24 and 05-21-03 in the CFM56-5B ESM, revision 

47, dated January 15, 2007, or later approved revision; 

(2) If the number of cycles accumulated since new by a LPT rear frame P/N 

338-171-703-0, 338-171-704-0, 338-171-705-0, 338-171-706-0 cannot be 

established, then within 300 cycles after the effective date of this directive, 

remove and replace the LPT rear frame, or perform the inspections in 

accordance with CFM56-5B Service Bulletin S/B 72-0620 initial issue, or 

later approved revision. 

Ref. Publications: CFM56-5B Engine Shop Manual chapter 05, revision 47 dated January 15, 

2007, or later approved revision 

CFM56-5B Service Bulletin S/B 72-0620 initial issue, or later approved revision 

Remarks: 1. If requested and appropriately substantiated, the responsible EASA 

manager for the related product has the authority to accept Alternative 

Methods of Compliance (AMOC) for this AD. 

2. This AD was posted on 18 May 2007 as PAD 07-086 for consultation until 

15 June 2007. The Comment Response Document can be found at 

http://ad.easa.europa.eu/ . 

3. Enquiries regarding this AD should be addressed to the AD Focal Point, 

Certification Directorate, EASA. E-mail: ADs@easa.europa.eu . 

4. For any questions concerning the technical content of the requirements in 

this AD, please contact: 

CFM International, 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