EASA AD No.: 2012-0241

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0241

Date: 12 November 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 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):

F28 aeroplanes

TCDS Number: EASA.A.037

Foreign AD: Not applicable

Supersedure: None

ATA 28 Fuel – Main Fuel Tanks Wiring – 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 under certain failure 

conditions of the wiring of the Overflow Valve Reed Switch, or the solenoid of 

the Level Control Pilot Valve (LCPV), or the solenoid of the Re/De-fueling ShutOff Valve, or the Collector-Tank Low Level Float-Switch, a short circuit may 

develop that causes a hot spot on the wiring conduit, or puncturing of the wiring

conduit wall in the main fuel tank. 

This condition, if not corrected, could create an ignition source in the main 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 fuses in 

the power supply wiring and/or return wiring for the main tank overflow valve 

reed-switches, the LCPV solenoid, the Re/De-fuel shut-off valve solenoid and 

the collector-tank Low Level float switch and subsequently, the implementation 

of the associated Critical Design Configuration Control Limitations (CDCCL).

Effective Date: 26 November 2012
EASA AD No.: 2012-0241

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) Within 24 months after the effective date of this AD, install fuses in the 

power supply wiring and/or return wiring for the main tank overflow valve 

reed-switches, the LCPV solenoid, the Re/De-fuel shut-off valve solenoid 

and the collector-tank Low Level float switch, in accordance with the 

Accomplishment Instructions of Fokker Services Service Bulletin (SB) 

SBF100-28-068.

(2) Prior to the modification as required by paragraph (1) of this AD, install a 

fuse in the LCPV wiring in accordance with the instructions of Fokker 

Services SBF100-28-042.

Note 1: The modification as described in Fokker Services SBF100-28-042 is 

already required by EASA AD 2010-0195, with a compliance time of 24 months 

after the effective date (13 October 2010) of that AD.

(3) CDCCL items: After modification of an aeroplane as required by 

paragraphs (1) and (2) of this AD, make certain that the wiring fuses 

remain installed on that aeroplane.

(4) Compliance with the requirement 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 CDCCL items in accordance with the information in 

paragraph 1.L.(1).(c) of Fokker Services SBF100-28-068,

and

(4.2) Complying with the approved aircraft maintenance programme

described in paragraph (4.1) of this AD.

Note 2: More information on this subject can be found in Fokker Services All 

Operators Message AOF100.167#04.

Ref. Publications: Fokker Services SBF100-28-068 dated 10 August 2012.

Fokker Services SBF100-28-042 dated 23 June 2010.

Fokker Services AOF100.167#04 dated 14 August 2012

The use of later approved revisions of these documents 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 09 October 2012 as PAD 12-129 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 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; facsimile +31-88-6280-111;

e-mail: technicalservices@fokker.com.

The referenced publication can be downloaded from 

www.myfokkerfleet.com.