E ASA AD No.: 20 1 4

- 00 99

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

- 0099

Date: 30 April 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) exemption]

. 

### Design Approval Holder’s Name:

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

F2 7 aeroplanes

TCDS Number: EASA.A.03 6

F oreign AD: Not applicable

Supersedure: None



### ATA 28 Fuel

– Fuel Tank s
– Modification [Fuel Tank Safety]

Manufacturer(s): Fokker Aircraft B.V.

Applicability: F2 7 Mark 200

, Mark 300, Mark 400, Mark 50 0, Mark 600 and Mark 700 aeroplanes

, all serial numbers

.

Reason: Prompted by an accident of a Boeing 747

- 131 (flight TWA800), the FAA published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/25/12. The review conducted by Fokker Services on the Fokker 27 design in response to these regulations revealed that no controlled bonding provisions are present on a number of critical locations, inside the fuel tan k or connected to the f uel t ank w all

, and no anti

- spray cover is installed on the F uelling S hut

- O ff V alve (FSOV) in both wing s

. This condition, if not corrected, could create an ignition source in the fuel tank vapour space, possibly result ing in a fuel tank explosion and consequent loss of the aeroplane. To address this potential unsafe condition, Fokker Services developed a set of bonding modifications and anti

- spray cover s , introduced with Service Bulletin (SB) SBF27

- 28

- 071 R evision 1 (R1)

, that require opening of the fuel tank access panels

. More information on this subject can be found in Fokker Services All Operators Message AOF 27.043#03.

For the reasons described above, this AD requires installation of additional bonding provisions

, and o f anti

- spray cover s on the FSOV

, that require opening of the fuel tank access panels

.

Effective Date: 14 May 2014E ASA AD No.: 20 1 4

- 00 99

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, install the additional bonding provisions and install an anti

- s pray cover on the FSOV in both w ing s in accordance with the Accomplishment I nstructions of the applicable Appendix

, dep ending on aeroplane serial number (s/n )

, to Fokker Services SBF 27

- 28

- 071 R1

. ( 2 ) Fuel A irworthiness Limitation items (A LI ) and Critical Design Configuration Control Limitations ( CDCCL ) : After modification of an aeroplane as required by paragraph (1) of this AD

, ensure that the additional bonding provisions and the a nti

- s pray c over on the FSOV in both wing s remain installed on that aeroplane in accordance with the information provided in paragraph 1.L.(1)(c) of the applicable Appendix (depending on aeroplane s / n) to Fokker Services SBF27

- 28

- 071R1

. ( 3 ) Compliance with the requirement of paragraph ( 2 ) of this AD can be demonstrated by: ( 3 .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:

I ncorporate the Fuel ALI and CDCCL related infor mation provided in paragraph 1.L.(1).(c) of the applicable Appendix ( depending on aeroplane s / n) to Fokker Services SBF 27

- 28

- 0 71 R1

, and ( 3 .2) Complying with the approved aircraft maintenance programme described in paragraph ( 3 .1) of this AD.

Ref. Public ations: Fokker Services SBF 27

- 28

- 071 R1 dated 06 March 201 4

. 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. This AD was posted on 07 January 201 4 as PAD 1 4

- 002 for consultation until 04 February 2013

, and republished on 14 April 2014 as PAD 1 4

- 002R1 for additional consultation until 28 April 2014

. No comments were received during the consultation periods.

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 conte nt of the requirements in this AD, please contact: F okker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL, Hoofddorp, The Netherlands; T elephone : +31

- 88

- 6280

- 350; Fax: +31

- 88

- 6280

- 111; E

- mail: technicalservices@fokker.com

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

.