EASA AD No.: 2013-0280

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/5 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0280

Date: 26 November 2013

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 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 accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, 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: None



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

Manufacturer(s): ATR-GIE Avions de Transport Région al (formerly Aerospatiale – Aeritalia, Aerospatiale – Alenia, Aerospatiale ATR – ALENIA, E ADS 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 MSN 1002 and 1005, and except those aeroplanes on which ATR mod 7152 has been embodied in production.

ATR 72-212A aeroplanes, all MSN, on which ATR mod 6 517 has been embodied in production, except MSN 1089, 1094, 1095 , 1097, 1098, 1099, 1100, 1101 and 1102, and except those aeroplanes on which ATR mod 7152 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 the surrounding passenger cabin furnishing was detected during a production
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.

For the reasons described above, this AD requires a one-time check of the gapEASA AD No.: 2013-0280

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/5 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. between the Type III Emergency Exit door internal s kin and a relevant fitting and, depending on findings, the accomplishment of a pplicable corrective action(s). This AD is considered to be a temporary measure and further actions may follow.

Effective Date: 10 December 2013

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:

(1) Within 2 months after the effective date of thi s AD, measure the gap between each Type III Emergency Exit door, left han d (LH) and right hand (RH), and the overhead stowage compartment fitting installed on the rail, by unlocking and slightly rotating the LH and RH Ty pe III Emergency Exit door, remaining 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 detect ed, 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 n ext flight, contact ATR to obtain approved repair instructions and acco mplish the repair accordingly.

Ref. Publications: ATR Service Bulletins:

ATR SB ATR42-25-0180 original issue, dated 19 Augus t 2013,

ATR SB ATR72-25-1141 original issue, dated 19 Augus t 2013.

The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

ATR42/72 IPC 25-23-02,

ATR42/72 AMM / JIC 52-21-00 RAI 10000.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.EASA AD No.: 2013-0280

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/5 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Commen ts, postponing the public consultation process until after publication

. 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

.EASA AD No.: 2013-0280

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 4/5 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Appendix 1: Illustrations

Figure 1: IPC 25-23-02 fig 87EASA AD No.: 2013-0280

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 5/5 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet.

Figure 2: Picture of an interference between the do or internal skin and the fitting