EASA AD No. 20 12
- 0119 EASA PAD No :11

CAP.00110
- 001 © 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 12 - 0119

Date: 04 Ju ly 2012
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 Euro pean 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 Age ncy [EC 2042/2003 Annex I, Pa rt 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 a eroplanes
TCDS Number : EASA.A.064
F oreign AD: Not app licable Supersedure: This AD supersedes DGAC France AD F
- 2005
- 108 (EASA approval 2005
- 6026 )

dated 28 June 2005

.



### ATA 28 Fuel System
– Magnetic Fuel Level Indicators
– Inspection /

Replacement / Repair
Manufacturer(s): Airbus (formerly A irbus I ndustri e ) 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
- 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 aeroplane s , all manufacturer serial numbers

. Reason: In 2005, s everal in
- service occurrences were reported of finding wear and/or detachment of the top stop of magnetic fuel level indicator s ( M FLI ), either observed during tank maintenance activities , or on MFLI returned to the MFLI manufacturer. T he investigation results indicated that the wear of the top stop retaining ‘S’ shaped wire had been caused by repetitive impact with the float , resulti ng in complete detachment of the top stop. This condition , if not detected and corrected , could lead an MFLI top stop to come into contact with a probe, which could, in the event of a lightning strike , create a n ignition source in the fuel tank vapour spa ce, possibly result ing in a fuel tank explosion and consequent loss of the aeroplane

. DGAC France issued AD F
- 2005
- 108 (EASA approval 2005
- 6026) to require identification (by inspection) and replacement of the affected metallic MFLI ( 3508802
- xx series wit h the ‘S’ shaped retaining wire ) with a metallic MFLI with the top stop retained by a ‘trapped wire’ , or with a composite MFLI. Since th at AD was issued, i t has been identified that the inspection procedureEASA AD No. 20 12
- 0119 EASA PAD No :11

CAP.00110
- 001 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. (visual check) detailed in Airbus Service Bulle tin ( SB ) A320
- 28
- 1138 was not fully effective , and that affected MFLI could still be fitted on aeroplane s which have passed the inspection in accordance with the instructions of this SB. For the reasons described above, this AD , which supersedes DGAC Franc e AD F
- 2005
- 108, requires a one - time inspection ( improved method ) to identify the type of MFLI installed and , depending on findings, replacement or repair , as applicable

. This AD also prohibits the installation of the affected MFLI on any aeroplane as repl acement parts. Effective Date: 1 8 July 2012 Required A ction(s) and Compliance Time(s) : Required as indicated , unless accomplished previously : (1) At the next scheduled fuel tank entry after the effective date of this AD, or w i thin 49 0 00 flight hours after 16 July 2005 [the effective date of DGAC France AD F
- 2005
- 108 ] , whichever occurs later , perform a special detailed inspect ion of the w ing t ank to determine which type of MFLI are installed in accordance with the instructions of Airbus SB A320
- 28
- 1209

. A review of aeroplane maintenance records is acceptable to make this determination, in lieu of the instruc tions of Airbus SB A320
- 28
- 1209 , provided that the P/N and the type of the installed MFLI can be conclusively identi fied from that review.

Table 1

– Affected MFLI Part Numbers 35 08802
- 24 3 5 08802
- 28 3 5 08802
- 75 3 5 08802
- 25 3 5 08802
- 34 3 5 08802
- 76 3 5 08802
- 26 3 5 08802
- 39 3 5 08802
- 91 3 5 08802
- 27 3 5 08802
- 74 Note: The affected MFLI have the ‘S’ shaped lock
- wire design

. ( 2) If a MFLI , identified as required by paragraph (1) of this AD, is installed with the ‘S’ shaped lock
- wire design ( Part Number (P/N) listed in Table 1 of this AD ) , within the compliance time defined in paragraph (1) of this AD , replace the affected MFLI with a serviceable part and accomplish the corrective actions (repair) , as applicable, in accordance with the instructions of Airbus SB A320
- 28
- 1209. For the purpose of this AD, a serviceable part is a composite MFLI , or a metallic MFL I with the top stop retained by a ‘trapped wire’ , as applicable to the location listed in Table 2 of this AD

. Table 2
- Metallic MFLI with the top stop retained by a ‘trapped wire’ ,

including applicable location (FIN) MFLI P/N Applicable Location (FIN) 3508802

‐ 35 56/57QM 3508802

‐ 36 58/59QM 3508802

‐ 37 60/61QM 3508802

‐ 38 62/63QM
(3) Aeroplanes on which Airbus modification (mod) 27496 has been embodied in production, and on which no wing tank MFLI replacement with a P/N listed in Table 1 of this AD , has been made since first flight, are not affected by the requirement of paragraph (1) of this AD.EASA AD No. 20 12
- 0119 EASA PAD No :11

CAP.00110
- 001 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. ( 4 ) After the effective date of this AD, do not install on any aeroplane a MFLI with a P/N listed in Table 1 of this AD Ref. Publications: Airbus SB A320
- 28
- 1209 original issue d ated 12 December 2011

. T he use of later approved revisions of this document is acceptable for compliance with the requirements of this AD. R emarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 23 April 2012 as PAD 1 2
- 0 33 and republished on 0 2 May 2012 as PAD 1 2
- 0 33 R1 for consultation until 2 1 May 201 2 . The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this A D 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 this AD, please contact: AIRBUS

– Airworthiness Office

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

.