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 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 AD applies, except in accordance with the requirements 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, -5B3/2P, -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, A321-112, 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 HPC stalls have been reported by operators of 

Airbus aeroplanes fitted with CFM International CFM56-5B engines since January 

2007. Root cause is highly deteriorated HPCs. To improve operability and 

maintainability, CFM International released 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 have 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 the 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 Temperature (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 2008-0228-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 installation 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 effective date of this AD 11 000 total 

hours or more since new or since a full HPC performance restoration: 

1.1 No later than 14 days from the effective 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 accordance 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 effectivity of CFM56-5B SB 73-0229, having 

accumulated at the effective date of this 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 effectivity of CFM56-5B SB 73-0229, having 

accumulated at the effective date of this 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 performance 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 substantiated, EASA can approve Alternative 

Methods of Compliance for this AD. 

2. The required actions and the risk allowance 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, 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 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.