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 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 aircra ft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an Airworthiness Directive applies, exc ept in accordance with the requirements of that Airworthine ss Directive unless otherwise specified by the Agency [EC 2042/2003 A nnex I, Part M.A.303] or agreed with the Authority of the Sta te 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) CFM 56-3 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 t he 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 & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any questions concerning the tech nical 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