EASA AD No.: 2013-0137

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0137

Date: 09 July 2013

Note: This Airworthiness Directive (PAD) 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:

AIRBUS

Type/Model designation(s):

A320 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD 2002-183 dated 03 April 2002.

ATA 53 Fuselage – Center Fuselage Transition and Pick Up Angle –

Inspection / Modification

Manufacturer(s): Airbus (Formerly Airbus Industrie)

Applicability: Airbus A320-111, A320-211, A320-212 and A320-231 aeroplanes, all 

manufacturer serial numbers, except those on which Airbus Modification 21202 

has been embodied in production. 

Reason: During the A320 fatigue test campaign, it has been determined that fatigue 

damage could appear on the transition and pick-up angle between Frame (FR) 

35 and FR36.

This condition, if not detected and corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, DGAC France issued AD 2002-183,

to require repetitive inspections of the center fuselage pick-up angle between 

FR35 and FR36, below stringer 30, left hand (LH) and right hand (RH) sides, 

and, depending on findings, accomplishment of applicable corrective action(s).

Since that AD was issued, a modification was developed, which has been 

published through Airbus Service Bulletin (SB) A320-53-1027 for in-service 

application, introducing additional washers below the riveting, which constitutes 

terminating action for the repetitive inspections.

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

France AD 2002-183, which is superseded, and requires modification of the

transition and pick-up angle between FR35 and FR36.

Effective Date: 23 July 2013
EASA AD No.: 2013-0137

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Re-statement of DGAC France AD 2002-183 requirements:

(1) Within the compliance time as specified in Table 1 of this AD, as 

applicable, and, thereafter, at intervals not to exceed 10 400 flight cycles 

(FC) or 24 600 flight hours (FH), whichever occurs first, inspect the center

fuselage transition and pick-up angle between FR35 and FR36 below 

stringer 30 LH and RH side in accordance with the instructions of Airbus 

SB A320-53-1028 Revision 01.

Table 1 – Initial Inspection

Compliance Time (whichever occurs later, A, B or C)

A

Before exceeding 10 400 FC or 24 600 FH, whichever occurs

first since aeroplane first flight.

B

Within 3 500 FC after 13 April 2002 [the effective date of DGAC 

France AD 2002-183], but not exceeding 16 000 FC since 

aeroplane first flight.

C

Within 12 000 FC after the last inspection as previously required 

by DGAC France AD 95-097-065.

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

damage is detected, before next flight, accomplish the applicable 

corrective actions in accordance with the instructions of Airbus SB A320-

53-1028 Revision 01.

New requirements of this AD:

(3) Before accumulation of 40 000 FC since aeroplane first flight, or within 1

500 FC after the effective date of this AD, whichever occurs later, but not 

exceeding 48 000 FC since aeroplane first flight, modify the aeroplane by 

installation of washers between the transition pick-up angle and the pin

nuts in accordance with the instructions of Airbus SB A320-53-1027 

Revision 03.

(4) Modification of an aeroplane before the effective date of this AD in 

accordance with the instructions of Airbus SB A320-53-1027 at original 

issue, or Revision 01, or Revision 02, is acceptable to comply with the 

requirements of paragraph (3) of this AD for that aeroplane.

(5) Modification of an aeroplane as required by paragraph (3) of this AD 

constitutes terminating action for the repetitive inspections required by 

paragraph (1) of this AD for that aeroplane.

Ref. Publications: Airbus SB A320-53-1027 original issue dated 01 March 1994, or Revision 01

dated 05 September 1994, or Revision 02 dated 08 June 1995, or Revision 03 

dated 12 February 2002.

Airbus SB A320-53-1028 Revision 01 dated 12 February 2002.

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 07 June 2013 as PAD 13-070 for consultation until 

05 July 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 
EASA AD No.: 2013-0137

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this AD, please contact: AIRBUS – Airworthiness Office – EIAS.

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