EASA AD No.: 2015-0171

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0171

Date: 20 August 2015

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 EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 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 [EU 

1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 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 Régional (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 1005. 

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 reported on an in-service aeroplane. 

Subsequent investigation identified chafed wiring between harnesses (2M-2S6M) and the metallic structure of the cargo lining panel above the electronic 
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rack 90VU shelf. The chafing was most likely the result of incorrect harness 

installation. In some cases, the bracket, which supports the harnesses, could 

be incorrectly positioned. Consequently, the wiring harnesses, and in certain 

configurations, the adjacent air duct, could be incorrectly routed. 

This condition, if not detected and corrected, could lead to wiring harness 

chafing and arcing, possibly resulting in an on-board fire. 

Prompted by this unsafe condition, EASA issued AD 2014-0052 (later revised) 

to require a one-time visual inspection of the affected area including a bracket 

position check and, depending on findings, accomplishment of applicable 

corrective actions. 

Since EASA AD 2014-0052R1 was issued, ATR determined that more 

aeroplanes are potentially affected (referred as Group 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 the requirements of EASA AD 

2014-0052R1, which is superseded, and requires inspection, and, depending 

on findings, applicable corrective action(s), on the adjusted range of 

aeroplanes. 

Effective Date: 03 September 2015 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(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 03, or ATR SB 

ATR72-92-1032 Revision 03, as applicable to aeroplane 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 [the 

effective date of EASA AD 2014-0052 at original issue] 

Group B Within 500 FH after the effective date of this 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 ATR42-92-0024 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 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. 
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(4) Depending on findings detected during the visual inspections as required 

by paragraphs (1.2) and (3) of this AD: 

(4.1) In case the bracket is found correctly positioned, 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 correctly positioned, 

within 500 FH after the inspection as required by paragraph (3) of 

this AD, accomplish the applicable corrective action(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, accomplished 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 comply with the 

requirements of this AD for that Group A aeroplane.

Ref. Publications: ATR SB ATR42-92-0024 original issue 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 2013, 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 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. 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 to the Safety Information 

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: 

ATR - GIE Avions de Transport Régional, 

Continued Airworthiness Service, 

Tel.: +33 (0)5 62 21 62 21 - Fax: +33 (0) 5 62 21 67 18; 

E-mail: continued.airworthiness@atr.fr.