EASA AD No.: 2015-0170

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0170

Date: 18 August 2015

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 EU 1321/2014 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

[EU 1321/2014 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 92 Electric and Electronic Common Installation – Cockpit Panel 

Bracket – Inspection

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, A320-211, 

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, except those on 

which Airbus modification (mod) 35869 has been embodied in production.

Reason: During an unscheduled maintenance operation on an A330 aeroplane, the 

10VU rack was removed for access and cracks were discovered on 10VU rack 

side fittings on lugs 1, 3 and 4. As a similar design is installed on A320 family 

aeroplanes, a sampling review was done to determine the possible fleet impact.

The result showed that several aeroplanes had cracked or broken 10VU rack 

side fittings.

This condition, if not detected and corrected, could lead to a high vibration level 

on the primary flight- and navigation displays during critical flight phases (takeoff and landing), possibly creating reading difficulties for the crew. 

Prompted by these findings, Airbus developed mod 35869 to reinforce the 

affected rack fitting lugs. For in-service aeroplanes, Airbus published Service 

Bulletin (SB) A320-92-1087 to provide inspection and repair instructions. 

For the reasons described above, this AD requires repetitive detailed 

inspections (DET) of the affected 10VU rack fitting lugs and, depending on 

findings, accomplishment of a repair.

Effective Date: 01 September 2015
EASA AD No.: 2015-0170

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time defined in Table 1 of this AD, and, thereafter, at 

intervals not to exceed 20 000 flight cycles (FC) or 40 000 flight hours 

(FH), whichever occurs first, accomplish a DET of the 10VU lugs in 

accordance with the instructions of Airbus SB A320-92-1087.

Table 1 – Initial Inspection

Compliance Time (whichever occurs later, A or B)

A

Before exceeding 30 000 FC or 60 000 FH, whichever occurs 

first since aeroplane first flight

B Within 24 months after the effective date of this AD

(2) If, during any DET as required by paragraph (1) of this AD, any crack is 

found, within the applicable compliance time as defined in paragraph 

1.E.(2) of Airbus SB A320-92-1087, accomplish the applicable corrective 

actions in accordance with the instructions of Airbus SB A320-92-1087.

(3) Repair of the 10VU rack lugs on an aeroplane, as required by paragraph 

(2) of this AD, does not constitute terminating action for the repetitive DET

as required by paragraph (1) of this AD for that aeroplane.

(4) Within 90 days after each DET as required by paragraph (1) of this AD,

report the results (including no findings) to Airbus.

Ref. Publications: Airbus SB A320-92-1087 original issue dated 28 March 2011, or Revision 01 

dated 17 May 2011, or Revision 02 dated 25 November 2014.

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 06 July 2015 as PAD 15-090 for consultation until 

03 August 2015. 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, Certification 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.