EASA AD No : 2009-0036 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009- 0036 

Date: 20 February 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 (CFM) 

Type/Model designation(s) : 

CFM56-3 turbofan engines 

TCDS Number : EASA.E.066 

Foreign AD : Not applicable 

Supersedure : None 

ATA 72 Engine – Fan Blades with 25 Degree Mid-span Shrouds –

Inspections 

Manufacturer(s): Snecma, General Electric 

Applicability: CFM International (CFM) CFM56-3 turbofan engines, all serial numbers, 

when equipped with fan blades - with 25 degree mid-span shrouds - Part 

Number (P/N) 9527M99P08, 9527M99P09, 9527M99P10, 9527M99P11, and 

1285M39P01, or fan blade pairs P/N 335-088-901-0, 335-088-902-0, 335-

088-903-0, and 335-088-904-0. 

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

737series aeroplanes. 

Remark: The installation of fan blades with 25 degree mid-span shrouds is 

not allowed on the CFM56-3C engine model.

Reason: An event of multiple fan blade failure has been reported on a CFM56-3 engine. 

Severe wear was observed on the underside of the fan blade platforms at the 

contact location with the fan blade dampers. This resulted in poor damping of the 

fan blade set and contributed to high dynamic stress of the blades. 

For the reasons stated above, this AD requires repetitive inspections of fan 

blades with 25 degrees mid-span shrouds as defined by CFM service bulletin 

CFM56-3/3B/3C S/B 72-1067 in order to reduce the risk of a multiple fan blade 

failure event which could result in an uncontained engine rotor failure. 
EASA AD No : 2009-0036 

EASA Form 110 Page 2/2 

Effective Date: 06 March 2009 

Required Action(s) 

and Compliance 

Time(s): 

(1) Within 3 months after the effective date of this AD, perform an inspection of fan 

blades P/N 9527M99P08, 9527M99P09, 9527M99P10, 9527M99P11, and 

1285M39P01, or fan blade pairs P/N 335-088-901-0, 335-088-902-0, 335-

088-903-0, and 335-088-904-0 in accordance with the accomplishment 

instructions of paragraphs 3.A (On-wing) or 3.B (In-shop) of CFM Service 

Bulletin (SB) CFM56-3/3B/3C 72-1067 original issue. 

If any damage is found, before further flight, remove and replace the blades as 

instructed in the accomplishment instructions of CFM SB CFM56-3/3B/3C S/B 

72-1067 original issue. 

(2) Accomplishment of inspections done in accordance with CFM Service Bulletin 

(SB) CFM56-3/3B/3C S/B 72-1067 original issue, within the last 3 000 engine 

Flight Cycles (FC) before the effective date of this AD satisfies the requirements 

of paragraph (1) of this AD. 

(3) Thereafter, at intervals not to exceed 3 000 engine FC from the last inspection, 

repeat the inspections required in paragraph (1) of this AD. 

(4) After the affective date of this AD, do not install on any CFM56-3 engine fan 

blades P/N 9527M99P08, 9527M99P09, 9527M99P10, 9527M99P11, and 

1285M39P01, or fan blade pairs P/N 335-088-901-0, 335-088-902-0, 335-

088-903-0, and 335-088-904-0 unless they have been previously inspected 

in accordance with paragraph 3 of the accomplishment instructions of CFM 

SB CFM56-3/3B/3C 72-1067 original issue. 

Ref. Publications: 

CFM service bulletin CFM56-3/3B/3C S/B 72-1067, original issue.

The use of later approved revisions of this document 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 27 January 2009 as PAD 09-025 for consultation 

until 17 February 2009.No comments were received during the 

consultation period. 

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 questions 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