EASA

EASAAD No: 2010-0156

AIRWORTHINESS DIRECTIVE

AD No.: 2010..()156

Date: 03 August 2010

Note: This Airworthiness Directiw (AD) is Issued by EASA, acting in accomancewith

Regulallon{EC) No 21fiJ20Q8 on behalf of the European Community, .ts Member Stales and

of the European third countries L'lal participate in the activities of EASA under fIrticIe 66 of

that Regula~OIl.

This AD is issued in aocordanc:e with EC 1702J2oo3, Part 21A.3B. In aceoroonce With EC 204212003 Annex t. Pan MA301. the

continuIng alrwOl'thlr.ess of an aircraft shall be ensured by aceompli5hing any appro:::able ADs. Consequen~y. no person trlZl ~:e

an aircraft to which an AD apelies. except in accordance with !he requirements of that AD, unless otherMse speolied by tIE ~

lEe 204212003 Annex I. Pill' M.A.303] 01'agreed with the Autnority of the Slate of Registry (EC 21snOO8. Article 14(4) exempl>:llli

Type Approval Holder's Name:

Fokker Services BV

Type/Model designation(s) :

F28 aeroplanes

reDS Number:

Foreign AD :

Supersedure:

ATA 28

Manufacturer(s):

Applicability:

Reason:

Effective Date:

EASA Form 110

EASAA037

Not applicable

None

Fuel- Outer Wing Upper Skin Panel Reinforcement StructureInspection I Rework [Fuel Tank Safety]

Fokker Aircraft B.V. (and predecessor companies)

F28 Mark 1000, 1000e, 2000, 3000, 3DDDe, 3000R, 3000RC and 4000

aeroplanes, all serial numbers.

Further to an accident of a Boeing 747·131 (flight TWA800), the FAA has

published Special Federal Aviation Regulation (SFAR) 88, and the JAA has

published Interim Policy INTtP0lJ25112. The design review conducted by

Fokker services on the Fokker F28 type design in response to these

regulations revealed that, under certain conditions, an ignition source may

develop in the wing lank vapour space, due to insufficient clearance between

the wiring along the Fuel Quantity Tank Units (FQTU's) and the local

reinforcing structure around the upper skin cut-out

This condition. if not correcled, in combination with flammable ruel vapours,

could result in a wing tank explosion and consequent loss of the aeroplane_

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

investigate if a clearance of 3 mm (0,12 inch) or more is available between

the FQTU probes wiring and the surrounding reinforcement structure of the

wing upper skin and corrective rework actions, depending on findings.

17 August 2010

Page 112
EASAAD No; 2010-0156

Required Aclion(s) Required as indicated, unless accomplished previouSly.

and Compliance (1) At a scheduled opening of the fuel tanks, but not laler than 84 months Time(s): after lhe effective dale of this AD, whichever occurs first, inspect the

upper wing skin FQTU hole reinforcement structure for Ihe minimum

clearance with the Fuel Quantity Indication probe wiring in accordance

with the Accomplishment Instructions of Fokker Services Service

Bulletin (SB) SBF28-57-D97.

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

minimum clearance is found to be insufficient, before next night. rework

the surrounding structure to remove the possibility of an ignition source,

in accordance with the Accomplishment Instructions of Fokker Services

SBF28-57-097.

Fokker Services SBF28-57-097 dated 06 May 2010.

Ref. Publications: The use of later approved revisions of this documenl is acceptable for

compliance with the requirements of this AD,

Remarks: ,. If requested and appropriately substantiated, EASA can approve

Alternative Methods of Compliance for this AD.

2. This AD was posted on 23 June 2010 as PAD 10-064 for consultation

until 21 July 2010. No comments were received during the consultation

period.

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

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

W¥f',v_myfokkertleel.com

EASAFonn 110 Page'lJ2