E ASA AD No : 20 12

- 0 123

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 12 - 0 123

Date: 0 9 July 2012

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 Euro pean 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, Pa rt 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

- 5 and

- 5B Engines
TCDS Number : EASA.E.003 and EASA. E.06 7 Foreign AD : Not applicable Supersedure : None



### ATA 73 Engine Fuel and Control

– Hydro - Mechanical Units
– Operational Limitation
Manufacturer(s): S NECMA , G eneral E lectric Applicability: CFM International CFM5 6

- 5 and CFM56

- 5B engines, all M odels, all serial numbers , when installed on an aeroplane operated under an air operator certificate issued by a national aviation authority of the Commonwealth of Independent States , i.e. Armenia, Azerbaijan, Belarus, Kazakhstan , Kyrgyzstan, Moldova, Russ ia, Taji kistan, Turkmenistan, Ukraine or Uzbekistan

. These engines are known to be installed on, but not limited to, Airbus A318, A319, A320 and A321 aeroplanes. Reason: Over the past 18 months, some A320 family aeroplanes, operated predominantly using TS

- 1 fuel, have experienced in

- flight shut downs (IFSD) resulting from hydro

- mechanical unit (HMU) failures. TS

- 1 fuel is mainly supplied in countries belonging to the Com monwealth of Independent States

. Investigation result s have determined that these HMU f ailures were caused by corrosion and consequential seizure of the HMU delta

- p valve. In addition, contaminants and corrosive catalysts have been detected within some TS

- 1 fuel samples. This condition, if not corrected, could lead to an increased IFSD rate , increasing the risk of an emergency landing , possibly resulting in damage to the aeroplane and injury to the occupants

. For the reasons described above, this AD prohibits the operational use of an HMU which has exceeded a certain number of hours in servi ce

. Effective Date: 2 3 July 2012E ASA AD No : 20 12

- 0 123

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) From 24 months after the effective date of this AD , do not operate an engine with an HMU th at has accumulated more than 10 000 hours , to be determined in accordance with the following criteria , whichever occurs later , (a), (b) or (c) : (a) engine hours since new , (b) engine hours since last HMU overhaul, (c) engine hours since last HMU maintenanc e in accordance with Section 3 Accomplishment Instructions of CFM International SB CFM56

- 5B 73

- 0122 (any revision), or CFM International SB CFM56

- 5 73

- 0182 (any revision), as applicable to engine type. ( 2 ) From the effective date of this AD, do not instal l an HMU on an engine, and do not install an engine on an aircraft, where the HMU accumulated time in service , determined as required by paragraph (1) of this AD, exceeds 10 000 engine hours. ( 3 ) The actions of paragraphs (1) and (2) of this AD are not re quired if it can be shown that the HMU has not been operated with more than 50% of TS

- 1 fuel during any 12

- month period , either since new, since overhaul, or since last maintenance in accordance with Section 3 Accomplishment Instructions of CFM Internation al SB CFM56

- 5B 73

- 0122 (any revision), or CFM International SB CFM56

- 5 73

- 0182 (any revision), as applicable to engine type , whichever occurs later

. Ref. Public ations: CFM International S

. A . SB CFM56

- 5B 73

- 0122 Revision 8 , and SB CFM56

- 5 73

- 0182 Revision 6 , both dated 08 March 2012. 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 f or this AD. 2. This AD was posted on 26 April 2012 as PAD 1 2

- 0 35 for consultation until 24 May 201 2

. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Exe cutive 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 Centre, Telep hone : +33 1 64 14 88 66 , Fax : +33 1 64 79 85 55 E

- mail : snecma.csc@snecma.fr , or CFM Inc. Aviation Operations Centre, Telephone: +1 513

- 552

- 3272, or +1 877

- 432

- 3272 , E

- mail : geae.aoc@ge.com

.