E ASA AD No.: 2013

- 0137

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 13

- 0 13 7

Date: 0 9 J u ly 201 3

Note: This Airworthiness Directive ( P 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 accordan ce 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 ope rate 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

F oreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD 2002

- 183 dated 03 April 2002

.



### ATA 53 Fuselage

– Center Fuselage T ransi tion 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 be tween Frame ( FR ) 35 and FR36

. This condition, i f not detected and cor rected
, could affect the structural integrity of the aeroplane.
To address this potential unsafe con dition, DGAC France issued AD 2002

- 183
, to require repetitive inspection s of the center fuselage pick

- up angle between FR 35 and FR 36
, below stringer 30
, left hand (LH) and right hand (RH) side s , 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 S ervice B ulletin (SB) A320

- 53

- 102 7 for in

- service application , intro ducing additional washers below the riveting , which constitutes terminating action for the repetitive inspections

. For the reasons describe d 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 2013E ASA AD No.: 2013

- 0137

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(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 FR 35 and FR 36 below stringer 30 LH and RH side in accordance with the instructions of Airbus SB A320

- 53

- 1028 Revision 0 1.

Table 1

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

A B efore exceeding 10 400 FC or 24 600 FH , whichever occurs first since aeroplane first flight.

B W ithin 3 500 FC a f te r 13 April 2002 [the effective date of DGAC France AD 2002

- 183 ], but n ot 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) I f, 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 instruction s of Airbus SB A320

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- 1028 Revision 0 1

. 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 n ot exceeding 48 000 FC since aeroplane first flight
, modify the aeroplane by installation of washers between the trans ition pick

- up angle and the pin nuts in accordance with the instruct ions of Airbus SB A320

- 53

- 1027 R evision 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 R evision 02
, is acceptable to comply with t he req uirements of paragraph ( 3 ) of thi s AD for that aeroplane

. (5) Modification of an aeroplane as required by paragraph ( 3 ) of this AD constitutes terminating action for the repetitive inspection s required by paragraph ( 1 ) of this AD for that aeroplane.

Ref. Public ations: 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 0 3 dated 12 February 20 0 2

. Airbus SB A320

- 53

- 1028 Revision 01 dated 12 February 2002

. The use of later approved revisions of th e s e document s 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 Jul y 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 inE ASA AD No.: 2013

- 0137

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. this AD, please contact: AI RBUS

– Airworthiness Office

– EIAS. Fax +33 5 61 93 44 51. E

- mail: account.airworth

- eas@airbus.com

.