EASA AD No : 2010-0159

EASA Form 110 Page 1/2

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0159

Date: 03 August 2010

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 EC 1702/2003, Part 21A.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].

Type Approval Holder’s Name :

Fokker Services B.V.

Type/Model designation(s) :

F28 Mark 0070 and Mark 0100 aeroplanes

TCDS Number : EASA.A.037

Foreign AD : Not applicable

Supersedure : None

ATA 28 Fuel – Wing Tank Overflow Valve Sense Line- & Wiring Conduit 

Hose Attachments – Inspection / Modification [Fuel Tank Safety]

Manufacturer(s): Fokker Aircraft B.V. 

Applicability: F28 Mark 0070 and Mark 0100 aeroplanes, all serial numbers.

Reason: Prompted by an accident of a Boeing 747-131 (flight TWA800), the Federal 

Aviation Administration (FAA) has published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) have published 

Interim Policy INT/POL/25/12. The review, conducted by Fokker Services on 

the Fokker 100 and Fokker 70 type design in response to these regulations, 

revealed that the fuel sense line from the overflow valves may touch the 

adjacent fuel-quantity indication-probe. Under certain conditions, this may result 

in an ignition source in the wing tank vapour space. 

This condition, if not detected and corrected, could result in a wing fuel tank 

explosion and consequent loss of the aeroplane.

For the reasons described above, this AD requires a one-time inspection to 

check the route and clamping of the sense line hose and wiring conduit hose to 

each wing tank overflow valve and, depending on the findings, the necessary 

corrective actions.

Effective Date: 17 August 2010
EASA AD No : 2010-0159

EASA Form 110 Page 2/2

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously.

(1) At a scheduled opening of the fuel tank, but not later than 84 months after 

the effective date of this AD, inspect the routing and clamping of the sense 

line hose and wiring conduit hose to each wing tank overflow valve in 

accordance with Part 1 of the Accomplishment Instructions of Fokker 

Services Service Bulletin (SB) SBF100-28-050.

(2) If, during the inspection as required by paragraph (1) of this AD, incorrect 

routing or clamping of the hoses are found, before next flight, install two 

brackets next to the overflow valve for the main tank access panel, make a 

modification to the routing of the hose for the sense line and install clamps 

to keep the hoses in position, in accordance with Part 2 of the 

Accomplishment Instructions of Fokker Services SBF100-28-050.

(3) After determining that the routing and clamping of the sense line hose and 

wiring conduit hose to each wing tank overflow valve on an aeroplane are 

correct, as required by paragraph (1) of this AD, or after modification of an 

aeroplane as required by paragraph (2) of this AD, as applicable, make 

certain that the sense line hose and wiring conduit hose to each wing 

overflow valve on that aeroplane remain routed and clamped in compliance 

with the requirements of this AD.

(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 for 

which the Operator or the Owner ensures the continuing 

airworthiness of each operated aeroplane:

Incorporate the CDCCL item in accordance with the information in 

paragraph 1.L.(1).(c). of Fokker Services SBF100-28-050,

and

(4.2) Complying with the approved aircraft maintenance programme 

described in paragraph (4.1) of this AD.

Ref. Publications: Fokker Services SBF100-28-050 dated 03 June 2010. 

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 01 July 2010 as PAD 10-069 for consultation until 

29 July 2010. No comments were received during the consultation period.

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail ADs@easa.europa.eu.

4. For any question concerning the technical aspects of the requirements in 

this AD, please contact:

Fokker Services B.V., Technical Services Dept., P.O. Box 231,

2150 AE Nieuw-Vennep, The Netherlands;

telephone +31 252-627-350; facsimile +31 252-627-211;

e-mail: technicalservices.fokkerservices@fokker.com

The referenced publication can be downloaded from 

www.myfokkerfleet.com