EASA AD No.: 2015-0171

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0171

Date: 20 August 2015

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, A rticle 14(4) exemption].


### Design Approval Holder’s Name: ATR-GIE AVIONS DE TRANSPORT RÉGIONAL Type/Model designation(s): ATR 72 and 42 aeroplanes

TCDS Number: EASA.A.084

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2014-0052R1 dated 07 April 2014.



### ATA 92 Electrical Routing – Electronic Rack 90 VU Shelf / Electrical Harness – Inspection

Manufacturer(s): ATR-GIE Avions de Transport Région al (ATR), formerly Aerospatiale – Aeritalia, Aerospatiale – Alenia, Aerospatiale ATR – ALENIA, EADS ATR – Alenia.

Applicability: Group A aeroplanes: ATR 42-400 and ATR 42-500 aeroplanes, Manufacturer Serial Numbers (MSN) 443 to 1006 inclusive, except MSN 811, 1002 and 100 5. ATR 72-102, ATR 72-202, ATR 72-212 and ATR 72-212A aeroplane models, MSN as listed below, except MSN 872, 887, 893, 956 and 1042: MSN 475 to 969 inclusive, MSN 971 to 988 inclusive, MSN 1025, MSN 1028 to 1069 inclusive, and
MSN 1072. Group B aeroplanes: ATR 42-500 aeroplane MSN 1014. ATR 72-102, ATR 72-202, ATR 72-212 and ATR 72-212A aeroplanes, MSN 1089 to 1175 inclusive, except MSN 1162.

Reason: An erroneous cockpit indication has been re ported on an in-service aeroplane. Subsequent investigation identified chafed wiring b etween harnesses (2M-2S6M) and the metallic structure of the cargo lining panel above the electronicEASA AD No.: 2015-0171

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. rack 90VU shelf. The chafing was most likely the re sult of incorrect harness installation. In some cases, the bracket, which sup ports the harnesses, could be incorrectly positioned. Consequently, the wiring harnesses, and in certain configurations, the adjacent air duct, could be inc orrectly routed. This condition, if not detected and corrected, coul d lead to wiring harness chafing and arcing, possibly resulting in an on-boa rd fire. Prompted by this unsafe condition, EASA issued AD 2 014-0052 (later revised) to require a one-time visual inspection of the affe cted area including a bracket position check and, depending on findings, accompli shment of applicable corrective actions. Since EASA AD 2014-0052R1 was issued, ATR determine d that more aeroplanes are potentially affected (referred as Gr oup B aeroplanes) than originally identified. It was also determined that some aeroplanes, originally addressed by AD 2014-0052, are not affected due to their specific configuration. Taking into account these findings, ATR issued Revision 03 of Service Bulletin (SB) ATR42-92-0024 and SB ATR72-92 -1032 to reflect the reidentified population of affected aeroplanes. For the reasons described above, this AD retains th e requirements of EASA AD 2014-0052R1, which is superseded, and requires insp ection, and, depending on findings, applicable corrective action(s), on th e adjusted range of aeroplanes.

Effective Date: 03 September 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within the compliance time as defined in Table 1 of this AD, accomplish concurrently the actions as specified in paragraphs (1.1) and (1.2) of this AD in the area above the electronic rack 90VU shelf , in accordance with the instructions of ATR SB ATR42-92-0024 Revision 0 3, or ATR SB ATR72-92-1032 Revision 03, as applicable to aeropla ne model: (1.1) Perform a visual inspection of the condition of the electrical wires of harnesses 2M-2S-6M, (1.2) Perform a visual inspection of the routing of electrical bundle 2M-2S6M and the routing of the air duct.

Table 1 – Visual Inspections
Aeroplanes Compliance Time

Group A Within 500 flight hours (FH) after 20 March 2014 [t he

effective date of EASA AD 2014-0052 at original iss ue] Group B Within 500 FH after the effective date of t his AD

(2) If, during the visual inspection as required by paragraph (1.1) of this AD, any damage is found on the electrical wire, before next flight, repair the wire in accordance with the instructions of ATR SB ATR42-92-0024 Revision 03 or ATR SB ATR72-92-1032 Revision 03, as applicable to aeroplane model. (3) If, during the visual inspection as required by paragraph (1.2) of this AD, the electrical bundle 2M-2S-6M and/or the air duct is found to be incorrectly routed, as defined in ATR SB ATR42-92-0 024 Revision 03 or ATR SB ATR72-92-1032 Revision 03, as applicable to aeroplane model, within the compliance time as specified in Table 1 of this AD, perform a visual inspection of the bracket position in accord ance with the instructions of ATR SB ATR42-92-0024 Revision 03 or ATR SB ATR72 -92-1032 Revision 03, as applicable to aeroplane model.EASA AD No.: 2015-0171

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. (4) Depending on findings detected during the visua l inspections as required by paragraphs (1.2) and (3) of this AD: (4.1) In case the bracket is found correctly positi oned, within the compliance time as specified in Table 1 of this AD, accomplish the applicable corrective action(s) in accordance with the instructions of ATR SB ATR42-92-0024 at Revision 03 or ATR SB ATR72 -92-1032 at Revision 03, as applicable to aeroplane model. (4.2) In case the bracket is found missing or not c orrectly positioned, within 500 FH after the inspection as required by p aragraph (3) of this AD, accomplish the applicable corrective actio n(s) in accordance with the instructions of ATR SB ATR42-92 -0024 Revision 03 or ATR SB ATR72-92-1032 Revision 03, as applicable to aeroplane model. (5) Inspections and corrective actions, accomplishe d on a Group A aeroplane before the effective date of this AD in accordance with the instructions of ATR SB ATR42-92-0024 original issue or Revision 01 or Revision 02, or ATR SB ATR72-92-1032 original issue or Revision 01 or Revision 02, as applicable to aeroplane model, are acceptable to co mply with the requirements of this AD for that Group A aeroplane.

Ref. Publications: ATR SB ATR42-92-0024 original is sue dated 06 June 2013, Revision 01 dated 16 January 2014, Revision 02 dated 17 April 2014 or Revision 03 dated 21 January 2015. ATR SB ATR72-92-1032 original issue dated 06 June 2 013, Revision 01 dated 16 January 2014, Revision 02 dated 17 April 2014 or Revision 03 dated 21 January 2015 The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 27 May 2015 as PAD 15-069 for consultation until 24 June 2015. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: ATR - GIE Avions de Transport Régional, Continued Airworthiness Service, Tel.: +33 (0)5 62 21 62 21 - Fax: +33 (0) 5 62 21 6 7 18; E-mail: continued.airworthiness@atr.fr

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