E ASA AD No : 20 11

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E ASA Form 11 0 Page 1 / 3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 1 1

- 0227

Date: 0 6 Dec em ber 201 1

Note: This Airworthiness Directive ( AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Eu ropean 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 Age ncy [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 aeroplanes

TCDS Number : EASA.A.037

Foreign AD : Not applicable

Supersedure : None



### ATA 28 Fuel

– Wing and Integral Center Wing Tanks

– Modification [Fuel Tank Safety]

Manufacturer(s): Fokker Aircraft B.V

.

Applicability: F28 Mark 0 070 and F28 Mark 0100 aeroplanes, all serial numbers (s/n)

.

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 o n the F okker 70 and Fokker 100 in response to these regulations revea led that the absence of electrical insulation material between a wing or I ntegral C enter W ing T ank (ICWT) Fuel Quantity Indication System ( FQIS ) probe and the bottom of the tank structure could, under certain conditions, result in an ignition source in the tank vapour space

. This condition, if not corrected, could result in a fuel tank explosion and consequent loss of the aeroplane.
For the reasons described above, this AD requires the appl ication of sealant below the FQIS probes in the wing tank s and below the FQIS probes in the ICWT

, as applicable to aeroplane configuration

. After modification, this AD requires repetitive inspections to verify that the sealant remains undamaged and, if damage is detected, repair or reapplication of sealant.

Effective Date : 2 0 December 2011E ASA AD No : 20 11

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E ASA Form 11 0 Page 2 / 3 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously.
(1) For F28 Mark 0070 and Mark 0100 aeroplanes, all s/n : At a scheduled opening of the fuel tanks, but not later t han 8 4 months after the effective date of this AD

, apply sealant below the probes in the wing tank s in accordance with the instructions of Part 1 of Fokker Services Service Bulletin (SB) SBF 100

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. (2) For F28 Mark 0070 and Mark 0100 aeroplanes s/n 114 42 through 11585 inclusive
, if equipped with an ICWT : A t a scheduled opening of the fuel tank , but not later than 8 4 months after the effective date of this AD, apply sealant below the probes in the ICWT in accordance with the instructions of Part 2 of Fok ker Services SBF100

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. Note: The sealant to be applied , as required by this AD, must be approved for the purpose. Refer to paragraph 2.B. of SBF100

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- 067 or contact Fokker Services for details.
( 3 ) Within 96 months a fter modification of an aeroplane as required by paragraph s (1) and (2) of this AD, as applicable to aeroplane configuration, and thereafter at intervals not to exceed 96 months

, inspect the ta n k structure below each FQIS probe in the wing tank s and

, if applicable

, below each FQIS probe in the ICWT

, to determine that the sealant coating is undamaged.
(4) If, during any inspection as required by paragraph (3) of this AD, damage is detected, before next flight, repair or reapply the coating

, in accordance with the instructions for the Fuel AL I in paragraph 1.L.(1).(c) of Fokker Services SBF100

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. Repair or reapplication of sealant does not constitute terminating action for the repetitive inspections require d by paragraph (3) of this AD.
(5) From the effective date of this AD, do not insta ll a FQIS probe in the wing tanks and, if applicable, in the ICWT, or install a wing tank cover and, if applicable

, an ICWT tank cover, unless the coating of sealant is in compliance with the requirements of this AD.
(6) Compliance with the requirements of paragraphs (3), (4) and (5) of this AD can be demonstrated by:
(6.1) Revising as follows the approved aircraft maintenance programme on the basis o f which the Operator or the Owner ensures the continuing airworthiness of each operated aeroplane:
Incorpor ate the Fuel ALI’s and CDCCL’s in accordance with the information in paragraph 1.L.(1)(c) of Fokker Services SBF100

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and
(6.2) Complying with the approved aircraft maintenance pro gramme described in paragraph (6 .1) of this AD.

Ref. Publications: F okker Services SBF 100

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. The use of later approved revisions of th is 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 A D was posted on 0 3 Nove m ber 2011 as PAD 11

- 1 14 for consultation until 0 1 December 2011. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquir ies 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 aspects of the requireme nts inE ASA AD No : 20 11

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E ASA Form 11 0 Page 3 / 3 this AD , please contact Fokker Services B.V., Technical Services Dept., P.O. Box 1 357

, 21 3 0 E L Hoofddorp , The Netherlands; telephone + 31 88

- 62 8

- 00 0 0; facsimile + 31 88

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- 0 1 1 1;

e

- mail : technicalservices@fokker. com

. The referenced publication can be downloaded from www.myfokkerfleet.com

.