EASA AD No : 2009-0110 

EASA Form 112 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0110 

Date: 07 May 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) : 

CFM56-5B turbofan engines 

TCDS Number : EASA.E.003 

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 (CFM) CFM56-5B1/P, -5B2/P, -5B3/P, -5B4/P, -5B5/P, 

-5B6/P, -5B7/P, -5B8/P, -5B9/P, -5B3/P1, -5B4/P1, -5B1/3, -5B2/3, -5B3/3, 

-5B4/3, -5B5/3, -5B6/3, -5B7/3, -5B8/3, -5B9/3, -5B3/3B1, -5B4/3B1 turbofan 

engines (CFM56-5Bn/P SAC and CFM56-5Bn/3) operating in commercial 

application and in corporate application (CFM56-5B Service Bulletin SB 

72-0308 applied) equipped with a low pressure turbine (LPT) rear frame part 

number (P/N) 338-171-751-0 and 338-171-752-0. 

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

A319, A320 and A321 series aeroplanes. 

Reason: The concerned LPT rear frame part numbers were introduced by the 

CFM56-5B Service Bulletin SB 72-0570 revision 02 issued 21 January 2008. 

They are obtained by modifying (reworking) older P/N. 

The issue of the CFM56-5B Engine Shop Manual (ESM) Temporary 

Revisions (TR) 05-0184, 05-0185, and 05-0186 in November 2008 introduced 

a life limit and mandatory inspection for the concerned LPT rear frames. 

In December 2008, ESM TR 05-0184 and 05-0185 were cancelled and 

superseded by ESM 05-0187 and 05-0188 which contain the same 

requirements for the concerned LPT rear frame. 

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 
EASA AD No : 2009-0110 

EASA Form 112 Page 2/2 

P/N and revise their aircraft maintenance programs accordingly.

Effective Date: 21 May 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 or mandatory inspections for LPT rear frame 

P/N 338-171-751-0 and 338-171-752-0, in accordance with the 

CFM56-5B ESM chapter 05 Temporary Revision (TR) 05-0186, 

05-0187 and 05-0188 applicable to the Engine Shop Manual 

Revision 52 or in accordance with subsequent revisions of the 

Engine Shop Manual that incorporate these Temporary Revisions. 

2) If the number of total engine cycles accumulated by a LPT rear 

frame P/N 338-171-751-0 and 338-171-752-0 cannot be positively 

established, then within 300 engine cycles after the effective date of 

the AD, remove and replace the LPT rear frame or perform the 

inspections in accordance with CFM56-5B Service Bulletin SB 

72-0620 revision 2. 

Note: The number of total engine cycles accumulated of the LPT rear frame 

is the sum of the number of engine cycles accumulated before and after 

compliance with CFM56-5B SB 72-0570.

Ref. Publications: 

CFM56-5B Engine Shop Manual chapter 05 Temporary Revisions (TR) 

05-0186, 05-0187 and 05-0188 applicable to the Engine Shop Manual 

Revision 52. 

Engine Shop Manual Revision 53 incorporates these Temporary Revisions. 

CFM56-5B Service Bulletin SB 72-0620 revision 2. 

The use of later approved revisions of the Service Bulletin 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 04 March 2009 as PAD 09-048 for consultation 

until 01 April 2009. 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