EASA AD No.: 2014-0099

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0099

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 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 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):

F27 aeroplanes

TCDS Number: EASA.A.036

Foreign AD: Not applicable

Supersedure: None

ATA 28 Fuel – Fuel Tanks – Modification [Fuel Tank Safety]

Manufacturer(s): Fokker Aircraft B.V.

Applicability: F27 Mark 200, Mark 300, Mark 400, Mark 500, 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 tank or connected to the fuel tank wall,

and no anti-spray cover is installed on the Fuelling Shut-Off Valve (FSOV) in both

wings. 

This condition, if not corrected, could create an ignition source in the fuel tank 

vapour space, possibly resulting 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 covers, introduced with Service Bulletin (SB) 

SBF27-28-071 Revision 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 AOF27.043#03.

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

bonding provisions, and of anti-spray covers on the FSOV, that require opening of 

the fuel tank access panels.

Effective Date: 14 May 2014
EASA AD No.: 2014-0099

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(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-spray cover 

on the FSOV in both wings in accordance with the Accomplishment 

Instructions of the applicable Appendix, depending on aeroplane serial 

number (s/n), to Fokker Services SBF27-28-071R1.

(2) Fuel Airworthiness Limitation items (ALI) 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 anti-spray cover on the 

FSOV in both wings 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:

Incorporate the Fuel ALI and CDCCL related information provided in 

paragraph 1.L.(1).(c) of the applicable Appendix (depending on 

aeroplane s/n) to Fokker Services SBF27-28-071R1,

and

(3.2) Complying with the approved aircraft maintenance programme 

described in paragraph (3.1) of this AD.

Ref. Publications: Fokker Services SBF27-28-071R1 dated 06 March 2014.

The use of later approved revisions of this 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 2014 as PAD 14-002 for consultation until 

04 February 2013, and republished on 14 April 2014 as PAD 14-002R1 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 content 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; Fax: +31-88-6280-111;

E-mail: technicalservices@fokker.com.

The referenced publications can be downloaded from 

www.myfokkerfleet.com.