EASA AD No : 2011-0183

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0183

Date: 23 September 2011

Note: This Airworthiness Directive (AD) is i ssued 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 acco mplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agenc y [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 24 Electrical Power – Galley Power Supply Wiring – Modification

Manufacturer(s): Fokk er Aircraft B.V.

Applicability: Fokker F28 Mark 0070 and Mark 0100 aeroplanes, serial number (s/n) 11340 through 11343, 11347, 11348, 11350 through 11356, 11359, 11360, 11361, 11367 through 11371, 11374 through 11378, 11382 through 11385, 11387 through 11390, 11394 through 11397, 11400 through 11423, 11425 through 11432, 11434 through 11439, 11441 through 11453 and 11456 through 11585.
Reason: Reports have been received about burned contacts in production break plug P 4259B and corresponding receptacle J 4259A. After investigation, it was concluded that the high electrical load on the contacts M, L and X, in combination with the electrical loads on the adjacent connections, may have resulted in these occurrences. This condition, if not detected and correc ted, can lead to overheating of the galley power supply wiring and/or the electrical connector and consequent smoke or fire in the galley area, possibly resulting in damage to the aeroplane and injury to occupants. For the reasons described above, this AD requires modification of the galley power supply wiring by disconnecting it from the affected plug/receptacle and reconnecting the power supply wiring through splices.

Effective Date: 07 October 2011EASA AD No : 2011-0183

EASA Form 110 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously.
Within 24 months after the effective dat e of this AD, modify the galley power supply wiring in accordance with the Accomplishment Instructions of Fokker Services B.V. Service Bulletin SBF100-24-044.
Ref. Publications: Fokker Services SBF100-24-044 dated 14 July 2011. 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 subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 24 August 2011 as PAD 11-093 for consultation until 21 September 2011. 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 tec hnical aspects of the requirements in this AD, please contact: Fokker Services B.V., Technica l Services Dept., P.O.Box 231, 2150 AE Nieuw-Vennep, The Netherlands; telephone +31 (0)252-627-350; facsimile +31 (0)252-627-211; e-mail: technicalservices@fokker.com

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

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