EASA AD No .: 20 1 4

- 0 10 6

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 4

- 0 10 6

Date: 0 7 May 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 accordance with E C 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:

FOKKER SERVICES B.V. Type/Model designation(s):

F2 8 aeroplanes

TCDS Number: EASA.A.03 7

F oreign AD: Not applicable

Supersedure: No ne



### ATA 28 Fuel

– Wing Fuel Tank

– Modification [Fuel Tank Safety]

Manufacturer(s): Fokker Aircraft B.V.

Applicability: F28 Mark 1000, 2000, 3000 and 4000 series aeroplanes, all serial numbers.

Reason: Prompted by an accident of a Boeing 747

- 131 (flight TWA800), the Federal Aviation Administration (FAA) published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) publishe d Inte rim Policy INT/POL/25/12. The review conducted by Fokker Services on the Fokker F28 design, in response to these regulations, revealed that insufficient measures were taken to ensure the correct locking of the attachment s of the Fuel Quantity Tank Units (FQTUs). When a FQTU becomes loose

, this could lead to insufficient clearance between the FQTU and the adjacent tank structure or other metal parts and, under certain conditions, create an ignition source inside the wing fu el tank vapour space.
This condition, if not detected and corrected, could result in a wing fuel tank explosion and consequent loss of the aeroplane. To address this potential unsafe condition, Fokker Services developed a modification to ensure that each FQTU remains properly attached

. For the reasons described above, this AD requires the application of sealant covering the nuts, washers and s tud ends at the FQTU attachment in each wing tank

. More information on this subject can be found in Fokker Services A ll O perators M essage AOF28.038#02.

Effective Date: 2 1 May 2014EASA AD No .: 20 1 4

- 0 10 6

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 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.
(1) At the next scheduled opening of the fuel tanks after the effective date of this AD

, apply sealant covering the nuts, washers and stud ends at the FQTU attachments in each main wing tank in accordance with the Accomplishment Instructions of Fokker Services S ervice Bulletin ( SB ) SBF 28

- 28

- 0 54 Revision 1

. (2) Modification of an aeroplane before the effective date of this AD in accordance with the Accomplishment Instructions of Fokker Services SBF28

- 28

- 054 at original issue is acceptable t o comply with the requirement s of paragraph (1) of this AD for that aeroplane

. (3 ) Fuel Airworthiness Limitation items (ALI) and Critical Design Configuration Control Limitations (CDCCL) items : After modification of an aeroplane as required by paragraph (1) of thi s AD, ensure that the additional sealant remain s installed on that aeroplane in accordance with the information provided in paragraph 1.L.(1)(c) of Fokker Services SBF28

- 28

- 054 Revision 1

. (4 ) Compliance with the requirement s of paragraph ( 3 ) of this AD can be demonstrated by:
(4 .1) Revising as follows the approved aircraft maintenance programme on the basis of which the operator or the owner ensures the continuing airworthiness of each operated aeroplane:
Incorporate the Fuel ALI and CDCCL items in acc ordance with the infor mation provided in paragraph 1.L .(1) (c) of Fokker Services SBF 28

- 28

- 0 54 R evision 1

, and ( 4

. 2) Complying with the approved aircraft maintenance pro gramme described in paragraph (4 .1) of this AD.

Ref. Publications: Fokker Services SB F 28

- 28

- 0 54 original issue dated 30 June 2010, or Revision 1 dated 09 January 201 4

. The use of later approved revisions of th is 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. This AD was posted on 02 April 2014 as PAD 14

- 06 1 for consultation until 30 April 2014. 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 th is AD, please contact: Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL, Hoofddorp, The Netherlands; T elephone +31

- 88

- 6280

- 350; F a x +31

- 88

- 6280

- 111; E

- mail: technicalservices@fokker. com

. The referenced publication can be downloaded from www.myfokkerfleet.com

.