EASA AD No.: 20 1 4

- 0 107

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 4
- 0 107

Date: 0 7 May 2014

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 ope rate 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.03 7

F oreign AD: Not applicable
Supersedure: None



### ATA 28 Fuel

– Main Fuel Tank Wiring

– Modification [Fuel Tank Safety]

Manufacturer(s): Fokker Aircraft B.V.

Applicability: F28 Mark 1000, 2000, 3000 and 4000 series 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 review conducted by Fokker Services on the Fokker F 28 design in response to these regulations revealed that , under certain failure conditions of the s olenoid of the l evel c ontrol p ilot v alve, the m ain t ank o verflow v alve reed s witch, the c ollector t ank l evel f loat s witch or the main tank fuelling shut

- o ff
v alve solenoid , a hot spot may develop in the tank. This condition, if not corrected, could create an ignition source in the main tank vapour space, possibly resulting in a fuel tank explosion and consequent loss of the aeroplane. To address this potential unsafe condition, Fokker Services developed a modification to the wiring (installation of fuses) of the a ffected components. For the reasons described above, this AD requires the installation of fuses in the wiring of the affected components and , subsequently, the implementation of the associated Critical Design Configuration Control Limitations (CDCCL) items

. More information on this subject c an be found in Fokker Services All O perators M essage AOF28.038#02.

Effective Date: 21 May 2014EASA AD No.: 20 1 4

- 0 107

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(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 wiring of the s olenoid of the l evel c ontrol p ilot v alve, of the m ain t ank o verflow v alve reed s witch, of the c ollector t ank l evel f loat switch , and of the main tank fuelling shut

- o ff v alve solenoid in accordance with the Accomplishment Instructions of the applicable ( depending on aeroplane s/n ) Appendix to Fokker Services Service Bulletin (SB) SBF 28

- 28

- 0 56

. (2) Prior to, or concurrent with, modification of an aeroplane as require d by paragraph (1) of this AD , modify the aeroplane in accordance with the A ccomplishment Instructions of Fokker Services SBF28

- 28

- 049 (installation of fuses in the c ollector t ank l evel f loat switch power supply wire) and of Fokker Services SBF28

- 28

- 051 ( install ation of fuses in the l evel c ont rol p ilot v alve power supply wire )

. Note: Accomplishment of the modifications specified in paragraph (2) of this AD is already required by EASA AD 2010

- 0194 and EASA AD 2010

- 0195 , respectively. ( 3 ) CDCCL items : After modification of an aeropla ne as required by paragraph s (1) and (2) of this AD , ensure that the wiring fuses remain installed on that aeroplane in accordance with the information provided in paragraph 1.L.(1)(c) of the applicable (depending on aeroplane s/n ) Appendix to Fokker Services SBF28

- 28

- 056

. (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: I ncorporate the CDCCL item s in accordance with the infor mation in paragraph 1 .L.(1) (c) of the applicable ( depending on aeroplane s /n ) Appendix to Fokker Services SBF 28

- 28

- 0 56 , and ( 4 .2) Complying with the approved aircraft maintenance programme described in paragraph ( 4 .1) of this AD.
Ref. Public ations: Fokker Services SB F 28

- 28

- 056 dated 09 January 2014

. Fokker Services SBF28

- 28

- 049 original issue dated 23 June 2010, or Revision 1 dated 09 January 2014. Fokker Services SBF28

- 28

- 051 original issue dated 23 June 2010, or Revision 1 dated 09 January 2014. The use of l ater approved revisions of these document s 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 02 April 2014 as PAD 14

- 06 2 for consultation until 30 April 2014. No comments were received during the consultation period. 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 requi rements in this AD, please contact: Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 E L, Hoofddorp, The Netherlands; T elephone +31

- 88

- 6280

- 350; F a x +31

- 88

- 6280

- 111; E

- mail: technicalservices@fokker.com

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

.