E ASA AD No.: 20 12

- 0 242

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 12

- 0 242

Date: 12 N o vem ber 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 European third countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with E U 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 8 aeroplanes

TCDS Number: EASA.A.03 7

F oreign AD: Not applicable

Supersedure: None



### ATA 28 Fuel

– Fuel Tank s
– Modification [Fuel Tank Safety]

Manufacturer(s): Fokker Aircraft B.V.

Applicability: F28 Mark 0070 and F28 Mark 0100 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 design review conducted by Fokker Services on the Fokker 70 and Fokker 100 in response to these regulations revealed that no controlled bonding provisions are present on a number of critical locations, inside the f uel t ank or connected to the f uel t ank w all.
This condition, if not corrected, may create an ignition source in the fuel tank vapour space, possibly resulting in a fuel tank explosion and consequent loss of the aeroplane.
For the reasons described above, this AD requires the installation of additional bonding provisions and

, subsequently, the implementation of the associated Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL)

.

Effective Date: 2 6 November 2012E ASA AD No.: 20 12

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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) Within 24 months after the effective date of this AD, install the additional bonding provisions in accordance with Part 3, 4, 5 and 6 of the Accomplishment I nstructions of Fokker Services Service Bulletin (SB ) SBF 100

- 28

- 0 69

. (2) At the next scheduled opening of the fuel tanks after the effective date of this AD, install the additional bonding provisions in accordance with Parts 1, 2, 7, 8 and 9 of the Accomplishment I nstructions of Fokker Services SBF 100

- 28

- 0 69

. (3) Fuel ALI and CDCCL: After modification of an aeroplane as required by paragraph (1) of this AD

, and a fter modification of an aeroplane as required by paragraph (2) of this AD

, respectively, e nsure that the additional bonding provisions , as applicab le, remain installed on that aeroplane in compliance with the requirements of this AD

. Note 1: The intent of paragraph (3) of this AD is that, d uring the interim period between the modifications of paragraph (1) and those of paragraph (2), whichever is done first, the Fuel ALI and CDCCL for those first installed bonding provisions are already applied. (4) Compliance with the requirements of paragraph (3) of this AD can be demonstrated by: ( 4 .1) Revising as follows the approved aircraft maintenance programme (AMP) on the basis of which the Operator or the Owner ensures the continuing airworthiness of each operated aeroplane: Incorporate the Fuel ALI’s and CDCCL’s in accord ance with the information in paragraph 1.L.(1)(c) of Fokker Services SBF100

- 28

- 069 ;

a nd (4.2) Complying with the approved AMP described in paragraph ( 4 .1) of this AD.

Note 2 : More information on this subject can be found in Fokker Services All Operators M essage AOF100.167#04.

Ref. Public ations: Fokker Services SB F 100

- 28

- 0 69 dated 1 7 August 2012

. Fokker Services AOF100.167#04 dated 14 August 2012

. The use of later approved revisions of th ese 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 0 9 October 2012 as PAD 12

- 1 30 for consultation until 06 November 2012

. 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, 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: Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL, Hoofddorp, The Netherlands; telephone +31

- 88

- 6280

- 350; facsimile +31

- 88

- 6280

- 111;

e

- mail: technicalservices@fokker.com

. The referenced publication can be downloaded from

www. myfokkerfleet.com

.