EASA AD No.: 2007-0276R1 

EASA Form 110 Page 1/3

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2007-0276R1 

[Correction 2: 12 April 2010] 

Date: 18 March 2010 

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) : 

A318, A319, A320 and A321 aeroplanes 

TCDS Number : EASA A.064 

Foreign AD : Not applicable 

Revision : This AD revises and replaces EASA AD 2007-0276 dated 26 October 2007. 

ATA 25 Equipment / Furnishing – 80VU Rack Attachments – Inspection / 

Repair / Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: 

Airbus A318-111, A318-112, 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, except those on which 

Airbus modification 34804 has been embodied in production, or which have 

been modified in-service in accordance with Airbus SB A320-25-1557 and 

Airbus SB A320-53-1215. 

Reason: 

Damage to the lower lateral fittings of the 80VU rack, typically elongated holes, 

migrated bushes, and/or missing bolts have been reported in-service. In 

addition damage to the lower central support fitting (including cracking) has 

been reported. 

In the worst case scenario a complete failure of the 80VU fittings in 

combination with a high load factor or strong vibration could lead to failure of 

the rack structure and/or computers or rupture/disconnection of the cable 

harnesses to one or more computers located in the 80VU. This rack contains 

computers for Flight Controls, Communication and Radio-navigation. These 

functions are duplicated across other racks but during critical phases of flight 

the multiple system failures / re-configuration may constitute an unsafe 

condition. 

For the reasons described above, EASA AD 2007-0276 was issued to require 

repetitive inspection of the lower lateral 80VU fittings for damage and the 
EASA AD No.: 2007-0276R1 

EASA Form 110 Page 2/3

inspection of the lower central 80VU support for damage and cracking, and the 

accomplishment of associated corrective actions, depending on findings. 

Since AD 2007-0276 was issued, Airbus introduced a new reinforced lower 

central support for the 80VU. 

This AD has been revised to introduce the new reinforced lower central 

support as an optional terminating action to the repetitive inspections. 

This AD has been republished a second time because the wrong file was used to 

publish the first one, correcting an error in Table 1. 

Effective Date: 

Revision 1: 18 March 2010 

Original issue: 09 November 2007 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated: 

(1) Repetitive inspection of the 80VU rack lower lateral fittings:

 Aeroplanes fitted with the 80VU rack lower lateral fittings modified in 

accordance with the instructions of Airbus SB A320-25-1557 are not 

affected by the inspections required by § (1) of this AD. 

(1.1) Unless accomplished previously, prior to the accumulation of 24 000 

Flight Cycles (FC) from the first flight or within 500 FC, whichever 

occurs later after 09 November 2007 [the effective date of the 

original issue of this AD], perform a special detailed inspection of the 

80VU rack lower lateral fittings using a boroscope, in accordance 

with the instructions of Airbus SB A320-25A1555. 

(1.2) Thereafter, at intervals not exceeding 4 500 FC, repeat the 

inspection in accordance with the instructions of Airbus SB A320-

25A1555. 

 In case the 80VU rack lower lateral fittings have been replaced as 

per Airbus SB A320-25A1555, within 24 000 FC after replacement of 

the fittings, perform the next inspection. 

(1.3) In case of findings during any of the inspections as required by § 

(1.1) or § (1.2) of this AD, apply corrective actions (inspection and/or 

repair, as necessary) in accordance with the instructions and 

timeframe given in Airbus SB A320-25A1555. 

(1.4) Accomplishment of corrective actions as required by § (1.3) of this 

AD does not constitute terminating action for the repetitive inspection 

requirements of § (1.2) of this AD. 

(2) Repetitive inspection of the 80VU rack lower central support:

(2.1) Unless accomplished previously, prior to the accumulation of 24 000 

FC after the first flight or within 500 FC, whichever occurs later after 

09 November 2007 [the effective date of the original issue of this 

AD], perform a special detailed inspection of the 80VU rack lower 

central support using a boroscope, in accordance with the 

instructions of Airbus SB A320-25A1555. 

(2.2) Thereafter, repeat this inspection in accordance with the instructions 

of Airbus SB A320-25A1555 at intervals as specified in Table 1 of 

this AD: 

Table 1 

Affected aeroplanes Inspection Interval not exceeding:

Aeroplanes fitted with a lower 

central support that has 

accumulated 30 000 FC or more 

500 FC 
EASA AD No.: 2007-0276R1 

EASA Form 110 Page 3/3

Aeroplanes fitted with a lower 

central support that has 

accumulated less than 30 000 

FC 

4 500 FC, without exceeding 30 750 

accumulated FC, thereafter 500 FC. 

 In case the 80VU rack lower central support has been repaired or 

replaced as per Airbus SB A320-25A1555 or Airbus SB A320-25-1557, 

perform the next due inspection within 24 000 FC from repair or 

replacement of the central support. 

(2.3) In case of findings during any inspection as required by § (2.1) or § 

(2.2) of this AD, apply corrective actions (replacement and/or repair, 

as necessary) in accordance with the following instructions and 

timeframe: 

(2.3.1) If a crack with a length more than 40 mm is found on the 

front or on the rear sheet (see Figure 3 Sheet 2 of Airbus SB 

A320-25A1555), or if a crack is found on the upper sheet 

(see Figure 3 Sheet 3 of Airbus SB A320-25A1555), before 

further flight, repair or replace 80VU rack the lower central 

support in accordance with the instructions of Airbus SB 

A320-25A1555 or SB A320-25-1557, as applicable. 

(2.3.2) If a crack with a length less than 40 mm is found on the front 

or on the rear sheet (see Figure 3 Sheet 2 of Airbus SB 

A320-25A1555), within 4 500 FC or 20 months, whichever 

occurs first after the finding, repair or replace the 80VU rack 

lower central support in accordance with the instructions of 

Airbus SB A320-25A1555 or Airbus SB A320-25-1557, as 

applicable. 

 Until the repair or replacement of the lower central support, 

repeat this inspection at intervals not exceeding 500 FC. 

(2.4) Repair or replacement of the 80VU rack lower central support as 

required by § (2.3) of this AD does not constitute terminating action 

for the repetitive inspection requirements of § (2.2) of this AD. 

(3) Modification of an aeroplane in accordance with the instructions of Airbus 

SB A320-53-1215 and SB A320-25-1557 terminates the repetitive 

inspection requirements of this AD for that aeroplane. 

Ref. Publications: 

Airbus Service Bulletin A320-25A1555 original issue. 

Airbus Service Bulletin A320-25-1557 original issue. 

Airbus Service Bulletin A320-53-1215 original issue. 

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 accept Alternative 

Methods of Compliance for this AD. 

2. The original issue of this AD was posted on 21 September 2007 as PAD 

07-173 for consultation until 05 October 2007. The Comment Response 

Document can be found at http://ad.easa.europa.eu/ . 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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 – EAS 

E-mail: account.airworth-eas@airbus.com .