EASA AD No.: 2009-0088R1

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0088R1

Date: 28 April 2009

Note: This Airworthiness Directive (AD) is i ssued 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 s hall be ensured by accomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the re quirements of that AD 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) :
CFM56-5B turbofan engines

TCDS Number : EASA.E.003

Foreign AD : Not applicable

Revision : This AD revises EASA AD 2009-0088 issued on 24 April 2009.



### ATA 72 Engine – High Pressure Compressor (HPC) – Inspection / Replacement

Manufacturer(s): Snecma, General Electric

Applicability: CFM56-5B1/P, -5B2/P, -5B3/P, -5B3 /P1, -5B4/P, -5B5/P, -5B6/P, -5B7/P, -5B8/P, -5B9/P, -5B4/P1, -5B1/2P, -5B2/2P, -5 B3/2P, -5B3/2P1, -5B4/2P, -5B4/2P1, -5B6/2P and -5B9/2P engines, all serial numbers, if operating with software version 5.B.Q (installed in accordance with CFM International Service Bulletin (SB) CFM56-5B 73-0219) or earlier software versions. These engines are known to be installed on, but not limited to the following aeroplane models: AIRBUS A318-111, A318-112, A319-111 , A319-112, A319-115, A320-214, A320-215, A320-216, A321-111, A321-1 12, A321-211, A321-212 and A321-213.
This AD is not applicable if engine software version 5.B.R (installed in accordance with CFM56-5B SB 73-0229) or later approved software versions are installed.

Reason: Several in service occurrences of HP C stalls have been reported by operators of Airbus aeroplanes fitted with CFM International CFM56-5B engines since January 2007. Root cause is highly deteriora ted HPCs. To improve operability and maintainability, CFM International releas ed Engine Control Unit software 5.B.Q in January 2007 which features 2 degrees additional Variable Stator Vanes closure in the low power region to increase the stall margin. This 5.B.Q software introduction has reduced the frequency of stalls; however, since April 2008, 12 different engines with this software hav e experienced stalls at 3 different operators.EASA AD No.: 2009-0088R1

EASA Form 110 Page 2/3 On 15 December 2008, a CFM56-5B powered Airbus A321 aeroplane experienced stalls on both engines during t he same flight. This event was caused by a high level of HPC deterioration.
Stalls on both engines during flight can cause a dual engine loss of thrust.
AD 2008-0227-E, applicable to CFM56-5B engines, was issued to require the EGT deterioration to be established, and for one of the engines to be replaced on aeroplanes with both engines indicating more than 80 degree Celsius (°C) of deterioration.
It was subsequently deemed necessary to mandate repetitive inspections, to reduce the deterioration threshold to 75°C, and to apply additional aeroplane level operational requirements. These actions were introduced by EASA AD 2008-0228-E, which superseded AD 2008-0227-E.
In February 2009, CFM introduced the 5.B.R software standard (CFM56-5B SB 73-0229) which provides additional stall margin and introduces a rating specific trim to limit the total Exhaust Gas Temp erature (EGT) deterioration. This will prevent HPC deterioration progressing to the level at which this type of stall event can occur. This software version is not applicable to Double Annular Combustor engine models.
EASA AD 2009-0088, superseding AD 2008-02 28-E, introduced limitations to the applicability, deleted aeroplane actions which were no longer necessary to prevent the identified unsafe condition and deleted redundant maintenance tasks. This AD also required the installation of 5.B.R software as a terminating action.
This Revision 1 is issued to clarify in the Required action and Compliance Time section of this AD that the installa tion of 5.B.R. software is required and terminates the repetitive requirements of this AD only for those engines to which CFM56-5B SB 73-0229 applies.
Effective Date: 08 May 2009

Required Action(s) and Compliance Time(s): Required as indicated unless accomplished previously in accordance with AD 2008-0227-E or AD 2008-0228-E:

1. For engines having accumulated at the e ffective date of this AD 11 000 total hours or more since new or since a full HPC performanc e restoration:
1.1 No later than 14 days from the e ffective date of this AD, determine the engine EGT margin deterioration in accordance with CFM International SB CFM56-5B 72-0722 Revision 01. Depending on the results, apply the relevant corrective actions in accor dance with paragraph 1.3. of this AD.
1.2 Repeat the determination of the engine EGT margin deterioration, at intervals not exceeding 800 Flight Cycles and, depending on the results, apply the relevant corrective actions in accordance with paragraph 1.3. of this AD.
1.3 For aeroplanes where both engines indicate more than 75°C EGT margin deterioration, within 30 days either remove one engine and replace it with an engine indicating less than 75°C EGT margin deterioration or install 5.B.R engine software in accordance with CFM56-5B SB 73-0229, if the engine is listed in the effectivity of CFM56-5B SB 73-0229.
1.4 For those engines listed in the effectivity of CFM56-5B SB 73-0229, accomplish CFM56-5B SB 73-0229 within 6 months from the effective date of this AD. The accomplishment of CFM56-5B SB 73-0229 terminates the repetitive requirements of this AD.EASA AD No.: 2009-0088R1

EASA Form 110 Page 3/3 2. For those engines listed in the effe ctivity of CFM56-5B SB 73-0229, having accumulated at the effective date of th is AD less than 11 000 total hours since new or since a full HPC performance restoration, accomplish CFM56-5B SB 73-0229 within 12 months from the effective date of this AD. The accomplishment of CFM56-5B SB 73-0229 terminates the repetitive requirements of this AD.
3. For those engines not listed in the e ffectivity of CFM56-5B SB 73-0229, having accumulated at the effective date of th is AD less than 11 000 total hours since new or since a full performance restoration, upon accumulation of 11 000 total hours since new or since a full HPC perfo rmance restoration, accomplish the requirements and the relevant corrective actions of paragraph 1.1, 1.2 and 1.3 of this AD.
4. After 12 months from the effective date of this AD, do not install any CFM56-5B engine listed in the effectivity of CFM56-5B SB 73-0229 on an aeroplane, unless in accordance with CFM56-5B SB 73-0229.

Ref. Publications: CFM56-5B S/B 72-0722 Revision 01 – CFM56-5B High Pressure Compressor 75 °C Degrees Performance Deterioration. CFM56-5B SB 73-0229 – 5.B.R Software. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately subs tantiated, EASA can approve Alternative Methods of Compliance for this AD.
2. The required actions and the risk a llowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication.
3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Research Section, Certific ation Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technica l 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.