EASA AD No.: 2015-0018

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.: 2015-0018

Date: 05 February 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 2013-0280 d ated 26 November 2013.



### ATA 25 Equipment / Furnishing – Type III Emergency Exit Do or – Modification

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

Applicability: ATR 42-500 aeroplanes, all manufactu rer serial numbers (MSN), on which ATR Modification (mod) 6518 has been embodied in produc tion, except those aeroplanes on which ATR mod 7294 has been embodied in production. ATR 72-212A aeroplanes, all MSN, on which ATR mod 6 517 has been embodied in production, except those aeroplanes on which ATR mod 7294 has been embodied in production.

Note: ATR mod 6517 and mod 6518 install the ‘Armoni a’ Cabin respectively on ATR 72-212A and ATR 42-500 aeroplane.

Reason: Interference between a Type III Emergency E xit door opening and surrounding passenger cabin furnishing was detected during a pr oduction check. Subsequent investigation identified an insufficient gap between the emergency exit door internal skin structure and the overhead stowage compartment fitting, installed on the rail, as a cause of the interferen ce. This condition, if not detected and corrected, coul d prevent an unobstructed opening of both Type III Emergency Exit doors in ca se of emergency evacuation. Prompted by this finding, EASA issued AD 2013-0280 to require a one-time check of the gap between the Type III Emergency Exi t door internal skin and aEASA AD No.: 2015-0018

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. relevant fitting and, depending on findings, the ac complishment of applicable corrective action(s). That AD was considered to be a temporary measure. Since that AD was issued, ATR developed a design so lution to ensure that no interference with surrounding structure occurs duri ng opening of an emergency exit. ATR Service Bulletins (SB) ATR42-25-0185, SB ATR42-25-0186, SB ATR72-25-1148 and SB ATR72-25-1149 were issued to p rovide the necessary modification instructions for in-service aeroplanes

. For the reason described above, this AD retains the requirements of EASA AD 2013-0280, which is superseded, and requires modifi cation of the overhead bin attachment adjacent to the Type III emergency exit doors.

Effective Date: 19 February 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Restatement of the requirements of EASA AD 2013-028 0 For all aeroplanes affected by this AD, except thos e aeroplanes on which ATR mod 7152 has been embodied in production and except MSN 1002, 1005, 1089, 1094, 1095, 1097, 1098, 1099, 1100, 1101 and 1102: (1) Within 2 months after 10 December 2013 [the eff ective date of EASA AD 2013-0280], measure the gap between each Type III E mergency Exit door, left hand (LH) and right hand (RH), and the overhea d stowage compartment fitting installed on the rail, by unloc king and slightly rotating the LH and RH Type III Emergency Exit door, remaini ng on their lower fittings. Use a shim gauge 6 mm (0.236 in) thick, to measure the gap between the doors internal skin and the relevant fittings, P/N S2522924620000 (LH) and P/N S2522924620100 (RH).
Note 1: For illustrations refer to the applicable A TR Illustrated Parts Catalogue (IPC) 25-23-02 fig 87 item 90/100 and to Appendix 1 of this AD.
Note 2: It might be necessary to locally pull on th e door blanket to correctly see the door internal skin. (2) If, during the measurement as required by parag raph (1) of this AD, a gap equal to or more than 6 mm (0.236 in) is detected, before next flight, reinstall the LH and RH Type III Emergency Exit door, in accordance with the instructions of the applicable ATR Aircraft Mainten ance Manual (AMM) / Job Instruction Card (JIC) 52-21-00 RAI 10000. (3) If, during the measurement as required by parag raph (1) of this AD, a gap less than 6 mm (0.236 in) is detected, before next flight, remove the fitting, P/N S2522924620000 LH or P/N S2522924620100 RH, as applicable, and measure the gap between the Type III Emergency Exit door internal skin, LH and RH, and the overhead stowage compartment hoo ks in accordance with the accomplishment instructions of ATR SB ATR4 2-25-0180 or ATR72-25-1141, as applicable to aeroplane model, an d, depending on findings, accomplish the follow-on actions as speci fied in paragraph (3.1) or (3.2) of this AD, as applicable. (3.1) If, during the measurement as required by par agraph (3) of this AD, a gap equal to or more than 6 mm (0.236 in) is dete cted, before next flight, re-install the LH and RH Type III Emergency Exit door in accordance with the instructions of ATR SB ATR42-25 -0180 or ATR SB ATR72-25-1141, as applicable to aeroplane model. (3.2) If, during the measurement as required by par agraph (3) of this AD, a gap less than 6 mm (0.236 in) is detected, before next flight, contact ATR to obtain approved repair instructions and accomplish the repair accordingly.EASA AD No.: 2015-0018

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. New requirements of this AD
For all aeroplanes affected by this AD : (4) Within 4 months after the effective date of thi s AD, modify the aeroplane in accordance with the instructions of ATR SB ATR42-25 -0185, or SB ATR42-25-0186, or SB ATR72-25-1148, or SB ATR72-25- 1149, as applicable to aeroplane model and configuration.

Ref. Publications: ATR SB ATR42-25-0180 original is sue, dated 19 August 2013, ATR SB ATR72-25-1141 original issue, dated 19 Augus t 2013, ATR SB ATR42-25-0185 original issue, dated 21 Novem ber 2014, ATR SB ATR42-25-0186 original issue, dated 21 Novem ber 2014, ATR SB ATR72-25-1148 original issue, dated 21 Novem ber 2014, ATR SB ATR72-25-1149 original issue, dated 21 Novem ber 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. This AD was posted on 12 December 2014 as PAD 14 -172 for consultation until 09 January 2015. The Comment Response Documen t can be found at http://ad.easa.europa.eu

. 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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