EASA AD No.: 20 14

- 0234 R1

TE. CAP.0011 0

- 00 4 © 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 14

- 0234 R1

Date: 11 December 2014

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 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) exempt ion].



### Design Approval Holder’s Name:

AIRBUS Type/Model designation(s):
A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable

Revision : This AD revises EASA AD 2014

- 0234 dated 24 October 2014 , including the

Correction dated 28 October 2014.



### ATA 28 Fuel

– Fuel Vent Protector

– Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318

- 111, A318

- 112, A318

- 121, A318

- 122, A 319

- 111, A 319

- 112, A 319

- 113, A 319

- 114, A 319

- 115, A 319

- 131, A 319

- 132, A 319

- 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 (MSN)

.

Reason: On each aeroplane wing, a NACA duct assembly is installed, including a Fuel Vent Protector (FVP) which is used as flame arrestor. T his FVP is maintained in its NAC A duct assembly by a circlip (also known as C

- clip)

. Following a wing water pressure test, the FVP is removed and dried with heat. During an inspection after this test, several circlip s were reported to be discoloured. Investigation reveal ed that a batch of circlips fitted on some FVP Part Number ( P/N ) 786 0 73

- 1

- 0 have an increased risk of corrosion due to a manufacturing quality issue

. This condition , if not detected and corrected, could lead to circlip failure and consequent FVP movement

, reduc ing the flame protector capa bility of the FVP cartridge

, possibly resulting in damage to the aeroplane in case of lightning impact or fire on ground

. For the reason describe d above, EASA issued AD 2014

- 0234 to require identification by serial number (s/n) of the affected FVP P/N 786 0 73

- 1

- 0 and removal from service

. This AD is revised t o clarif y that only maintenance records since August 2012 should to be consulted to demonstrate , as required by paragraph (2), that no replacement FVP has been installed

.EASA AD No.: 20 14

- 0234 R1

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: Revision 1: 18 December 2014
Original issue: 07 November 2014

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:

Note: The FVP affected by this AD are those having P/N 786 0 73

- 1

- 0 , having a s/n as listed in Appendix 1 of this AD, and are not marked with “Amdt B”.
(1) For an aeroplane having a MSN as listed in Table 1 of this AD, w ithin 30 months , or 7 500 f light h ours, or 5 000 f light c ycles, whichever occurs first since Airbus date of manufacture of the aeroplane, inspect each FVP P/N 786 0 73

- 1

- 0 on the aeroplane to determine whether it is an affected FVP, and replace each affected FVP with a serviceable pa rt in accordance with the instructions of Airbus Service Bulletin (SB) A320

- 28

- 1221

.

Table 1

- Affected A eroplane s listed by MSN

5438, 5441, 5444, 5445, 5447, 5457, 5459, 5460, 5461, 5463, 5464, 5469, 5473 to 5478 inclusive , 5481, 5482, 5483, 5485 to 5488 incl u sive , 5490 to 5493 inclusive , 5495 to 5505 inclusive

, 5507 to 5515 inclusive , 5517, 5518, 5520 to 5527 inclusive

, 5530, 5536, 5539, 5541, 5544, 5547, 5551, 5553 and 5556

.

(2) For a n aeroplane having a MSN not listed in T able 1 of this AD

, no action is required by this AD, provide d it is determined that no affected FVP ha s been installed on that aeroplane after July 2012

. In case an affected FVP is installed, or no s/n identification can be made, within 12 months a f te r 07 November 2014 [ the effective date of the original issue of this AD ]

, replace the FVP with a serviceable part in accordance with the instructions of Airbus SB A320

- 28

- 1221

. (3) A review of aeroplane delivery or maintenance records is acceptable to identify the FVP s/n, in lieu of the inspection as required by paragraph (1) of this AD, or in lieu of the determination as required by paragraph (2) of this AD, as applicable, provided those records can be relied upon for that purpose, and the s/n of the FVP can be conclusively identified from that review

. ( 4 ) From 07 November 2014 [ the effective date of the original issue of this AD ]

, it is allowed to install on any aeroplane a FVP P/N 786 0 73

- 1

- 0 having a s/n as listed in Appendix 1 of this AD

, provided the FVP is marked with “ Amdt B ”

.

Ref. Public ations: Airbus SB A320

- 28

- 1221 original issue dated 21 July 2014

. The use of later approved revisions of th i s 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. Th e original issue of th is AD was posted on 05 September 2014 as PAD 14

- 13 8 for consultation until 03 October 2014 . 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, Certificatio n 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

.EASA AD No.: 20 14

- 0234 R1

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet.



### Appendix 1

– Affected FVP P/N 786 0 73

- 1

- 0 ( manufactured during August 2012 )

s/ n 786073IN 0 XXXX (last f our digits shown in this Table only)

3752 3821 3868 3911 3966 4010

3753 3826 3871 3914 3967 4011

3754 3827 3874 3922 3969 4013

3755 3829 3877 3925 3971 4017

3756 3830 3878 3927 3972 4019

3757 3833 3882 3930 3977 4023

3758 3834 3893 3937 3978 4024

3759 3836 3897 3938 3980 4025

3760 3839 3898 3940 3981 4026

3761 3840 3899 3945 3982 4039

3787 3848 3900 3946 3983 4048

3788 3849 3901 3947 3984 4065

3810 3850 3904 3948 3985 4066

3812 3851 3905 3951 3986 4068

3814 3853 3906 3961 3987 4070

3817 3859 3907 3962 3996 4184

3819 3860 3908 3964 3997 4187

3820 3867 3910 3965 4009