EASA AD No.: 2013-0087

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0087

Date: 09 April 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 42 and ATR 72 aeroplanes

TCDS Number: EASA A.084

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2009-0159-E dated 20 July 2009.

ATA 56

Windows – Cockpit Forward Side Windows – Inspection / 

Replacement

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

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

Applicability: ATR 42 and ATR 72 aeroplanes, all certified models, all manufacturer serial 

numbers. 

Reason: In 2009, a Left-Hand (LH) forward side glass window of an ATR 72-212 

aeroplane blew out while performing a ground pressure test. The investigation 

results revealed some anomalies on the forward side window at the level of the 

z-bar on the windows external side and at the level of the inner retainer on the 

windows internal side. Such anomalies are considered as precursors of this 

kind of failure. Air or water leakages between the z-bar and the outer glass ply, 

or between the inner retainer and inner glass ply indicate the presence of

deteriorating structural components in the window.

Neither ATR nor PPG Aerospace have authorized repairs on the window z-bar

or z-bar sealant. Any attempted repairs on these forward side window z-bars

and/or z-bar sealants could lead to a similar event as described above.

In-flight loss of a forward side window would cause rapid cabin decompression, 

possibly resulting in flight crew incapacitation and consequent reduced control, 

or loss of control of the aeroplane, and cause the risk of injury to persons on 

the ground. The loss of a forward side window while the aeroplane is on the

ground, due to differential cabin pressure, could result in injury to aeroplane

occupants or to persons outside the aeroplane.

To address this potential unsafe condition, EASA issued AD 2009-0159-E to 
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require repetitive inspections of the affected LH and right-hand (RH) cockpit 

forward side glass windows and, in case discrepancies are found as defined in 

PPG Aerospace Service Bulletin (SB) NP-158862-001, the replacement of the 

window(s).

Since that AD was issued, a cockpit forward RH-side window blew out during 

flight on an ATR72-212 aeroplane. Degradation of the window is considered to 

have been the cause for this failure.

For the reasons described above, this AD retains the requirements of EASA AD 

2009-0159-E, which is superseded, adds another inspection interval of 750 

flight cycles (FC) and requires to accomplish the inspections in accordance with 

the instructions of Revision 1 of PPG Aerospace SB NP-158862-001, which

provides more information on examples of discrepant conditions.

This AD also requires the removal from service of the affected Part Number 

(P/N) NP158862-1 and P/N NP158862-2 cockpit forward side windows, which 

constitutes terminating action for the repetitive inspections required by this AD.

Effective Date: 23 April 2013

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless already accomplished:

(1) For all ATR 42 and ATR 72 aeroplanes that are equipped with PPG 

Aerospace cockpit forward side glass windows P/N NP158862-1 and/or 

P/N NP158862-2: Within 2 000 FC since first installation of the cockpit 

forward side window on an aeroplane, or within 10 days after the effective 

date of this AD, whichever occurs later, and, thereafter, at intervals not 

exceeding 550 flight hours (FH) or 750 FC, whichever occurs first, inspect 

the cockpit forward side window to detect any damage or discrepancies in 

accordance with the instructions of PPG Aerospace SB NP-158862-001 

Revision 1.

Note1: If, for a given cockpit forward side window, the FC accumulated since its 

first installation on an aeroplane cannot be established, the total FC 

accumulated by the aeroplane must be used to determine the compliance time 

for the initial inspection of the affected cockpit forward side window.

(2) If, during any inspection as required by paragraph (1) of this AD, one of the 

conditions, as specified in Table 1 of this AD, is found, reduce the interval 

of the inspection as required by paragraph (1) to 50 FC or 7 days, 

whichever occurs later.

Table 1 – Detected Conditions

a. sealant separation between the Z-bar and the outer glass ply, 

with depth less than 4 mm (0.160 in)

b. sealant separation between inboard retainer and inner glass 

ply, with depth less than 7,5 mm (0.300 in) and cumulative 

length less than 300 mm (12.000 in)

c. window showing both sealant separation between the Z-bar 

and the outer ply, and separation between inboard retainer and 

inner glass ply, common to the same holes location with a 

length less than 225 mm (8.860 in), and not covering the entire 

arc of a window corner

(3) If, during any inspection as required by paragraph (1) or (2) of this AD, any 

discrepant condition, as defined in PPG SB NP-158862-001 Revision 1, is 

found, before the next pressurized flight, or within 10 days after the 

inspection, whichever occurs first, replace the affected window(s) in 

accordance with the instructions of ATR42/72 Job Instruction Card AMM 
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JIC 56-12-00 RAI 10000.

Note 2: For unpressurized flight conditions and limitations, refer to ATR Master 

Minimum Equipment List (MMEL) item 21-30-1 and Dispatch Deviation Guide 

(DDG) item 21-30-1.(4)

(4) Within 30 days after each inspection where damage or discrepancies are

found, submit a detailed report of the findings to ATR.

(5) Replacement of a cockpit forward side window as required by paragraph 

(3) of this AD with a cockpit forward side window P/N NP158862-1 (LH) or 

P/N NP158862-2 (RH), as applicable, does not constitute terminating 

action for the repetitive inspections required by this AD.

(6) Before 01 January 2020, replace each PPG Aerospace P/N NP-158862-1 

(LH) and P/N NP-158862-2 (RH) cockpit forward side window with another 

approved cockpit forward side window. For alternative window installations, 

consult ATR documentation, or contact ATR. Modification of an aeroplane

by replacing both PPG Aerospace P/N NP158862-1 (LH) and P/N 

NP158862-2 (RH) cockpit forward side windows with other approved 

windows constitutes terminating action for the repetitive inspections 

required by this AD for that aeroplane.

(7) From 01 January 2020, do not install on any aeroplane PPG Aerospace 

P/N NP158862-1 (LH) or P/N NP158862-2 (RH) cockpit forward side 

windows.

Ref. Publications: PPG Aerospace SB NP-158862-001 Revision 1 dated 10 January 2013.

The use of later approved revisions of this document is acceptable for

compliance with the requirements of this AD.

ATR42/72 Job Instruction Card AMM JIC 56-12-00 RAI 10000.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 12 March 2013 as PAD 13-046 for consultation until 

26 March 2013. No comments were received during the consultation 

period.

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.