EASA AD No.: 2014-0052R1

TE.CAP.00110-003 © 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.: 2014-0052R1

Date: 07 April 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e activities 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 EC 2042/2003 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 accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Design Approval Holder’s Name:

ATR-GIE AVIONS de TRANSPORT RÉGIONAL Type/Model designation(s): ATR 72 and ATR 42 aeroplanes

TCDS Number: EASA A.084

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2014-0052 dated 0 6 March 2014.



### ATA 92 Electrical routing – Electronic Rack 90VU Shelf / E lectrical

Harness – Inspection

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

Applicability: ATR 42-400 and ATR 42-500 aeroplanes models, from Manufacturer Serial Number (MSN) 443 up to 1006 inclusive, except MSN 8 11, 1002 and 1005. ATR 72-102, ATR 72-202, ATR 72-212 and ATR 72-212A aeroplanes models, MSN as listed below, except MSN 956 and 1042: - from MSN 475 up to 969 inclusive, - from MSN 971 up to 988 inclusive, - MSN 1025,

- from MSN 1028 to 1069 inclusive and MSN 1072.

Reason: An erroneous cockpit indication has been re ported on an in-service aircraft. Subsequent investigation identified chafed wiring b etween harnesses (2M-2S-6M) and the metallic structure of the cargo lining panel above the electronic rack 90VU shelf. The chafing was most li kely the result of incorrect harness installation. In some cases, the bracket, w hich supports the harnesses, could be incorrectly positioned. Consequ ently, the wiring harnesses, and in certain configurations, the adjac ent air duct, could be incorrectly 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.EASA AD No.: 2014-0052R1

TE.CAP.00110-003 © 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. To address this potential unsafe condition, ATR iss ued Service Bulletin (SB) ATR42-92-0024 and SB ATR72-92-1032, as applicable t o aeroplane model, to provide inspection instructions. For the reasons described above, EASA issued AD 201 4-0052 to require a one-time visual inspection of the affected area inc luding a systematic bracket position check and, depending on findings, accompli shment of applicable corrective actions. This AD is revised to make the bracket position che ck dependent on findings, determined during the inspection of the electrical bundle and air duct routing.

Effective Date: Revision 1: 07 April 2014 Original issue: 20 March 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 500 flight hours (FH) after 20 March 201 4 [the effective date of original issue of this AD], accomplish concurrently the actions of the paragraphs (1.1), (1.2) and (1.3), in the area abov e the electronic rack 90VU shelf, in accordance with the instructions of ATR SB ATR42-92-0024 Revision 1, or ATR SB ATR72-92-1032 Revision 1, as applicable to aeroplane model: (1.1) Visually inspect the condition of the electri cal wires of harnesses 2M-2S-6M, (1.2) [deleted] (1.3) Visually inspect the routing of electrical bu ndle 2M-2S-6M and the routing of the air duct. (2) If, during the visual inspection, as required b y paragraph (1.1) of this AD, any damage is found on the electrical wire, before next flight, repair the wires in accordance with the instructions of ATR SB ATR42-92-0024 Revision 1 or ATR SB ATR72-92-1032 Revision 1, as a pplicable to aeroplane model. (3) [deleted] (4) If, during the visual inspection, as required b y paragraph (1.3) of this AD, electrical bundle 2M-2S-6M and/or the air duct is f ound to be incorrectly routed, as defined in ATR SB ATR42-92-0024 at Revis ion 1 or ATR SB ATR72-92-1032 at Revision 1, as applicable to aerop lane model, within the compliance time as required by paragraph (1) of this AD, visually inspect, the bracket position in accordance with th e instructions of ATR SB ATR42-92-0024 Revision 1, or ATR SB ATR72-92-103 2 Revision 1, as applicable to aeroplane model. (5) Inspections and corrective actions, accomplishe d before 20 March 2014 [the effective date of original issue of this AD] i n accordance with the instructions of ATR SB ATR42-92-0024 original issue or ATR SB ATR72- 92-1032 original issue, as applicable to aeroplane model, are acceptable to comply with the requirements of this AD. (6) Depending on findings detected during visual in spections as required by paragraphs (1.3) and (4) of this AD: (6.1) In case the bracket is found correctly positi oned, within the compliance time as required in paragraph (1) of thi s AD, accomplish the applicable corrective action(s) in a ccordance with the instructions of ATR SB ATR42-92-0024 at Revisio n 1 or ATR SB ATR72-92-1032 at Revision 1, as applicable to ae roplane model. (6.2) In case the bracket is found missing or not c orrectly positioned, within 500 FH after the inspection as required by p aragraph (4) ofEASA AD No.: 2014-0052R1

TE.CAP.00110-003 © 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. this AD, accomplish the applicable corrective actio n(s) in accordance with the instructions of ATR SB ATR42-92 -0024 at Revision 1 or ATR SB ATR72-92-1032 at Revision 1, a s applicable to aeroplane model.

Ref. Publications: ATR SB ATR42-92-0024 original is sue, dated 06 June 2013 or Revision 1 dated 16 January 2014. ATR SB ATR72-92-1032 original issue, dated 06 June 2013 or Revision 1 dated 16 January 2014. 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. The original issue of this AD was posted on 15 J anuary 2014 as PAD 14-009 for consultation until 12 February 2014. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive 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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