EASA AD No.: 2013-0280

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2013-0280

Date: 26 November 2013

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 EC 2042/2003 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 [EC 

2042/2003 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: None 

ATA 25 Equipment / Furnishing – Type III Emergency Exit Door – 

Inspection / Modification 

Manufacturer(s): ATR-GIE Avions de Transport Régional (formerly Aerospatiale – Aeritalia, 

Aerospatiale – Alenia, Aerospatiale ATR – ALENIA, EADS ATR – Alenia). 

Applicability: ATR 42-500 aeroplanes, all manufacturer serial numbers (MSN), on which ATR 

Modification (mod) 6518 has been embodied in production, 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 6517 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 ‘Armonia’ Cabin respectively on 

ATR 72-212A and ATR 42-500 aeroplane. 

Reason: Interference between a Type III Emergency Exit 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 interference. 

This condition, if not detected and corrected, could prevent an unobstructed 

opening of both Type III Emergency Exit doors in case of emergency 

evacuation. 

For the reasons described above, this AD requires a one-time check of the gap 
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between the Type III Emergency Exit door internal skin and a relevant fitting 

and, depending on findings, the accomplishment of applicable 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 previously: 

(1) Within 2 months after the effective date of this AD, measure the gap 

between each Type III Emergency Exit door, left hand (LH) and right hand 

(RH), and the overhead stowage compartment fitting installed on the rail, 

by unlocking and slightly rotating the LH and RH Type 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 ATR 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 the door blanket to correctly see 

the door internal skin. 

(2) If, during the measurement as required by paragraph (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 Maintenance Manual (AMM) / 

Job Instruction Card (JIC) 52-21-00 RAI 10000. 

(3) If, during the measurement as required by paragraph (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 hooks in accordance 

with the accomplishment instructions of ATR SB ATR42-25-0180 or 

ATR72-25-1141, as applicable to aeroplane model, and, depending on 

findings, accomplish the follow-on actions as specified in paragraph (3.1) 

or (3.2) of this AD, as applicable. 

(3.1) If, during the measurement as required by paragraph (3) of this AD a 

gap equal to or more than 6 mm (0.236 in) is detected, 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 paragraph (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. 

Ref. Publications: ATR Service Bulletins: 

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

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

The use of later approved revisions of these documents 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, EASA can approve 

Alternative Methods of Compliance for this AD. 
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2. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive 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. 

 
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Appendix 1: Illustrations 

Figure 1: IPC 25-23-02 fig 87 
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Figure 2: Picture of an interference between the door internal skin and the fitting