EASA

EASA AD No. 20HI-Q139

AIRWORTHINESS DIRECTIVE

AD No. 2010-0139

Date: 01 July 2010

NOle: This Airworthir.ess Directive (AD) is Issued by EASA, aCling in accordance with

Regulation ECl N~ 21612~ on behalf ~f.the European C<:,mmunily, Its Member States and

of the European third countries that parliClpale In the act,v.~es of EASA under Article 66 of

lhat Regul'fion,

Thl$ AD is issued in accon:Iance with EC 170mOO3, Part 21A.3B. In a<:cordance with EC 204212O'J3 Anne~ l. Pall MA301, t."e

COlltinuing afrworminess of an alrctall shall be ensured by accomplishing ~ applicable ADs. Cansequen"v. no person may operate

an aircr-aft to whicl1 an AD applies. except in a~ with the requiJemeflts QI thaI AD, Ul'l1ezs o!herwlse specified by the AgencylEe 204212003 Annex l. PM M,A.303] or agreedwil\1the Authority of !he SlateQl Regislty IEC 21612003, Artiele l<l(<lJ exemptionJ.

Type Approval Holder's Name:

Fokker Services B.V.

TypefModel designation(s) :

F28 aeroplanes

TeDS Number:

Foreign AD :

Supersedure'

ATA 28

Manufacturer(s):

Applicability:

Reason:

Effective Date:

EASA Form 110

EASA.A.037

Nol applicable

None I

I

Fuel- FuJlling Control Panel eam -Inspection J Replacement

Functional Check {Fuel Tank Safety]

Fokker AirC(aft B.V. and predecessor companies.

,

F28 Marks 1000, 1000c, 2000, 3000, 3OODC,3OO0R, 3000RC and 4000

aeroPlanes'lall serial numbers. if equipped with a Centre Wing Tank (CWT),

and F28 Mark 0100 aeroplanes, serial numbers 11244 through 11441.

Prompted b~ an accident of a Boelng 747-131 (flight TWA800), the FAA

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

Aviation AU~horities (JAA) pUblished Interim Policy INTfPOU25/12. The

design reviiw conducted by Fokker on the F28 in response to these

regulations revealed that, in case of a lightning strike, an ignition source can

develop in the wing tank vapour space during fuel transfer from bag lank

CWT, if the blectrical power for refuelling is not switched off after refuelling.

Service ex~rience has revealed situations where the power switch of the

Fuelling Control Panel (FCP) appeared' to be ·ON" with the access panel

closed. The eam on the access panel that should operate the power switch.

if forgotten by flight crew or maintenance staff, can pivot away during closing

of the panel, which may result in the switch staying in the "ON" position.

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

consequent loss Of the aeroplane.

For the reasbns described above, this AD requires an inspection of Ihe earn

and, depending on findings. replacement with an improved part.

Subsequently, this AD requires repetilive functional checks of the carn and,

depending 9n findings, the necessary corrective actions.

15 July 201p

Page 113
EASA AD No' 2010-0139

Required as indicated, unless accomplished previously_

(1) INithin 6 months after the effective date of1his AD, inspect the FCP earn,

identi~ the Part Number (PIN) and, if the correct PIN is installed,

perform a functional check to verify that it operates correctly, in

accord~nce with the instructions of Part 1 of Fokker Services Service

Bulleti~ SBF28-28-052 or SBF100-28-063, as applicable to the

aeroplane model.

(2) If the I~spection as required by paragraph (1) of this AD reveals that an

Incorrept PIN carn Is installed, wilhin 24 months after the effective date

of this ~D, replace the incorrect PIN earn with a correct PIN earn and

perfoon a functional check 10verify that it operates correctly, in

accord~nce with the Instructions of Part 2 of Fokker Services SBF28-28-

052 Of SBF1OQ-28-063, as applicable to the aeroplane model.

(3) If during any functional check as required by paragraphs (1) and (2) of

this AD, the cam does not operate correctly. before next night, adjust the

earn until it operates correctly, in accordance with Part 2 of the

Accomplishment Instructions of Fokker Services SBF28-28-052 or

SBF100-28-063, as applicable to the aeroplane model.

(4) VVilhin ~ 200 flight hours (FH) after verification that the earn operates

correc~y, as required by paragraphs (1), (2) and (3) ofthis AD, as

Required Action(s) appiicaFle, and thereafter at intervals not to exceed 1 200 FH, perform

and Compliance a funcitonal check to verify that the earn operates correctly and,

Tlme(s): depen~ing on findings, before nexi night, take appropriate corrective

actions, in accordance with the instructions for the Fuel All in paragraph

1.L,(1 )(c) of Fokker Services SBF28-28-052 or SBF1 00·28-063, as

applicable 10the aeroplane model, Corrective aclion does no! constitute

termin~ting action for ihe repetitive checks as required by paragraph (4)

of this AD.

(5) From the effective dale of this AD. do not instal! an FCP access door,

earn or Fuelling Panel on any aeroplane, unless in compliance with the

requirements of this AD.

(6) ComPli1nce with the requirements of paragraphs (4) and (5) of this AD

can be demonstrated by:

(6.1) Revising as follows the approved aircraft maintenance programme

fO~hi'h the 000""0' 0' <heOwoe, e"",,, the ooo';ou;og

OIl orthiness of each operated aeroplane:

In orporate the Fuel All's and CDCCL's in accordance with lhe

informalion in paragraph 1.L.(1 )(c) of Fokker Services SBF28-28-

052 or SBF 100-28-063, as applicable to the aeroplane model.

I

"d

(6.2) CbmPIYing wtlh the approved aircraft maintenance programme

described in paragraph (6.1) of this AD.

Fokker Services SBF28-28-052 dated 20 April 2010.

Fokt;er Services SBF1OQ-28-063 dated 15 April 2010.

Ref. Publications: The use of later approved revisions of these documents is acceptable for

compliance with the requirements of Ihls AD.

1. If reque~ted and appropriately substantiated, EASA can approve

2.

Alterna~ve Methods of Compliance for this AD.

This A~was posted on 31 May 2010 as PAD 10-055 and republished on

Remarks: 09 Jun 2010 as PAD 10--055R1, for consultation until 28 June 2010. No

3.

comme lIS were received during the consultation period.

Enquiries regarding this AD should be referred to the Airworthiness

Directiv~s, Safety Manaoement & Research Section, Certification

EASAForml10 Page 213
EASA AD NQ: 2010-0139

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

this ADI please contact:

FokkerlServices BV, Technical Services Dept., P,D.Bo.\( 231,

2150 A~ Nieuw-Vennep, The Netherlands;

telephore (31) 252.-627-350: facsimile (31) 252-627-211:

e-mall: tectmicalservices, fokkerservices@fokker.com

The referenced publication can be downloaded from

www.myfokkerfleel.com

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