EASA AD No : 2011-0231

EASA Form 110 Page 1/2

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0231

Date: 09 December 2011

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 1702/2003, Part 21A.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].

Type Approval Holder’s Name :

AIRBUS

Type/Model designation(s) :

A319, A320 and A321 aeroplanes

TCDS Number : EASA.A.064

Foreign AD : Not applicable

Supersedure : None

ATA 53 Fuselage – Windshield Central Lower Node Continuity Fittings –

Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A319-112, A319-113, A319-132, A320-211, A320-212, A320-214, 

A320-231, A320-232, A321-111 and A321-131 aeroplanes models, 

manufacturer serial numbers 0259, 0260, 0264, 0266 to 0270 inclusive, 0275, 

0276, 0278, 0287, 0296, 0300, 0303, 0312, 0320, 0321, 0323, 0325, 0328, 

0332, 0334, 0335, 0337, 0346, 0352, 0353, 0356, 0365, 0369, 0375, 0377, 

0382, 0383, 0396, 0398, 0401, 0412, 0413, 0416, 0419, 0421, 0431, 0432, 

0438, 0440, 0441, 0445, 0453, 0458, 0459, 0466, 0468, 0473, 0474, 0482, 

0484, 0491, 0493, 0497, 0498, 0501, 0502, 0505, 0507, 0509, 0518, 0520, 

0521, 0529, 0531, 0534, 0537, 0538, 0544, 0549, 0554, 0555, 0560, 0563, 

0577, 0578, 0585, 0598, 0600, 0608, 0612, 0618, 0621, 0625, 0637, 0660, 

0685, 0976, 1010, 1092, 1096, 1103, 1139, 1143, 1158, 1251, 1356 and 

1511.

Reason: One operator reported finding two fatigue cracks on continuity fittings at lefthand (LH) and right-hand (RH) sides at the front windshield lower framing on 

an A319 aeroplane on which Airbus modification (mod.) 22058 had been 

embodied in production. Airbus mod. 22058 (which is included in Airbus mod.

21999) was introduced to improve the fatigue strength of the windshield front 

framing by increasing the thickness of framing flanges adjacent to the

concerned fittings.

Further analyses have demonstrated that the damage tolerance and fatigue 

requirements of JAR 25.571 (b) are not met on aeroplanes in post-mod.

22058 configuration.

This condition, if not detected and corrected, could reduce the structural 

integrity of the affected aeroplanes.
EASA AD No : 2011-0231

EASA Form 110 Page 2/2

For the reasons describe above, this AD requires, as a first step, for 

aeroplanes that are above or close to the threshold, a one-time High 

Frequency Eddy Current (HFEC) inspection of the windshield central lower 

node continuity fittings to detect cracks, the reporting of the inspection results 

and, depending on findings, the accomplishment of associated corrective 

actions.

This inspection will be extended to all post mod. 22058 and post mod. 21999 

Airbus A318/A319/ A320/A321 aeroplanes with repetitive inspection 

requirements in the next Airbus A318/A319/ A320/A321 Airworthiness 

Limitations Section (ALS) part 2 revision.

Effective Date: 23 December 2011

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Before the accumulation of 34 000 flight cycles (FC) since aeroplane first 

flight, or within 4 500 FC after the effective date of this AD, whichever 

occurs later, accomplish an HFEC inspection of the windshield central 

lower node continuity fittings at LH and RH sides in accordance with the 

instructions of Airbus Service Bulletin (SB) A320-53-1245 Revision 01.

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

cracks are detected, before next flight, contact Airbus for approved repair 

instructions and accomplish those instructions accordingly.

(3) Within 30 days after the accomplishment of the HFEC inspection as 

required by paragraph (1) of this AD, report the results, including no

findings, to Airbus.

(4) Aeroplanes which have passed the HFEC inspection and applied the

associated corrective actions before the effective date of this AD, in 

accordance with the accomplishment instructions of Airbus SB A320-53-

1245 at original issue, are compliant with the requirements of paragraphs 

(1) and (2) of this AD. Within 30 days after the effective date of this AD, 

report the results of the inspection, including no findings, to Airbus.

Ref. Publications: Airbus Service Bulletin A320-53-1245 Revision 01 dated 17 May 2011.

The use of later approved revisions of this document 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 03 November 2011 as PAD 11-112 for 

consultation until 01 December 2011. 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.