EASA AD No.: 2013-0011

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0011

Date: 15 January 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 EC 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:

AIRBUS

Type/Model designation(s):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 56 Windows – Cockpit Sliding Window Seals – Inspection / 

Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, 

A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, 

A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, 

A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, 

A321-231 and A321-232 aeroplanes, all manufacturer serial numbers.

Reason: Several occurrences have been reported on A320 family aeroplanes of PPG

sliding windows that were difficult to operate after landing. 

The investigation results revealed that when a seal having Part Number (P/N)

22-17-7640-1 or P/N 22-17-7640-2 is installed on a sliding window, closure of 

the window can create a vacuum between the 2 tubes of the pressure seal, 

leading to the window remaining stuck to the frame on the fuselage side, due to 

suction effect.

This condition, if not detected and corrected, could lead to the functional loss of 

the sliding window as an exit, possibly preventing the flight crew from safely 

evacuating the aeroplane during an emergency.

For the reasons described above, this AD requires a one-time detailed 

inspection (DI) of the sliding windows and its seal to identify the affected sliding 

window seals and, depending on findings, accomplishment of the applicable

corrective actions.

Effective Date: 29 January 2013
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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 750 flight cycles or 750 flight hours or 4 months, whichever occurs 

first after the effective date of this AD, accomplish a DI of the left-hand (LH) 

and right-hand (RH) sliding windows and sliding window seals in order to 

identify the P/N of each window and seal in accordance with the 

instructions of Airbus Service Bulletin (SB) A320-56-1016.

A review of aeroplane maintenance records is acceptable to make this 

determination, in lieu of the instructions of Airbus SB A320-56-1016, if the 

P/N and manufacturing dates of the installed sliding windows and sliding 

window seals can be conclusively identified from that review.

(2) If, during the DI as required by paragraph (1) of this AD, a sliding window 

P/N is identified as listed in Table 1 of this AD without modification 

amendment M, and sliding window seals P/N 22-17-7640-1 or P/N 22-17-

7640-2 are installed, before next flight, modify the sliding window seal in 

accordance with the instructions of Airbus SB A320-56-1015.

Table 1 – Affected PPG Sliding Windows P/N

LH RH

NP165312-1 NP165312-2

NP165312-3 NP165312-4

NP165312-5 NP165312-6

NP165312-7 NP165312-8

NP165312-9 NP165312-10

NP165312-11 NP165312-12

(3) For sliding windows, identified as affected as required by paragraph (2) of 

this AD, replacement of a sliding windows seal P/N 22-17-7640-1 (LH) or

P/N 22-17-7640-2 (RH) with a seal P/N 22-17-7640-3 (LH) or P/N 22-17-

7640-4 (RH), respectively, is an acceptable alternative method to comply 

with the modification requirement of paragraph (2) of this AD. The 

replacement of the window seals can be accomplished in accordance with 

the sliding window installation/removal instructions as provided in the 

Airbus A318/A319/A320/A321 Aircraft Maintenance Manual, sub section 

56-12-11, Page Block 401.

(4) Aeroplanes on which Airbus modification 153512 (installation of sliding 

window with P/N NP165312-13 and NP165312-14 with improved seal) or 

modification 153534 (installation of sliding window with P/N NP165312-11 

and NP165312-12 with amendment M) has been embodied in production

are not affected by the requirements of paragraphs (1) and (2) of this AD, 

provided that no sliding window or sliding window seal has been replaced

since first flight.

(5) Aeroplanes on which Airbus modification 39587 (installation of affected 

seal on PPG sliding windows) has not been embodied in production are 

not affected by the requirements of paragraphs (1) and (2) of this AD, 

provided that no sliding window or sliding window seal has been replaced

since first flight.

(6) From the effective date of this AD, do not install on an aeroplane any PPG 

sliding window with a P/N listed in Table 1 of this AD with a seal having 

P/N 22-17-7640-1 or P/N 22-17-7640-2, unless the seal has been modified 

in accordance with the instructions of Airbus SB A320-56-1015, or PPG SB 

165312-56-001.

Ref. Publications: Airbus SB A320-56-1015 original issue dated 14 September 2012.
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Airbus SB A320-56-1016 original issue dated 14 September 2012.

PPG Aerospace SB 165312-56-001 original issue dated 29 February 2012.

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 28 November 2012 as PAD 12-154 for consultation 

until 31 December 2012. The Comment Response Document can be found 

at http://ad.easa.europa.eu.

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: AIRBUS – Airworthiness Office – EIAS,

Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com.