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 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 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 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]. 

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): Fokker 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 corrected, 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 2011 
EASA 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 date 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 substantiated, 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 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 (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.