EASA AD No : 2011-0083 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0083 

Date: 12 May 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) : 

F27 and F28 aeroplanes 

TCDS Number : EASA.A.036 and EASA.A.037 

Foreign AD : Not applicable 

Supersedure : None 

ATA 24 Electrical Power – Electrical Power Center (EPC) and Battery 

Relay Panel – Inspection / Adjustment 

Manufacturer(s): Fokker Aircraft B.V. 

Applicability: F27 Mark 050, Mark 0502 and Mark 0604 aeroplanes, all serial numbers. 

F28 Mark 0070 and Mark 0100 aeroplanes, all serial numbers. 

Reason: In December 1989, Fokker issued Service Bulletin (SB) SBF50-24-A013 and 

SBF100-24-A011 (both Alert Bulletins) to instruct operators to inspect and 

adjust several torque values of bus bars and contactors in the EPC. The Civil 

Aviation Authority of The Netherlands (CAA-NL, formerly RLD) issued AD 

(BLA) 89-159 and BLA 89-157 respectively (both now at issue 2), to require 

operators of the affected aeroplanes to comply with the instructions of these 

SBs. 

Since those ADs were issued, several operators have reported finding loose 

nuts on contactors in the EPC of Fokker 50/60 aeroplanes in post-SBF50-24-

A013 configuration and on Fokker 70/100 aeroplanes in post-SBF100-24-

A011 configuration. In some cases, the findings included damaged (burned) 

contactors. 

This condition, if not detected and corrected, could lead to arcing and, in 

combination with other factors, to an onboard fire, possibly resulting in 

damage to the aeroplane and injury to occupants or maintenance personnel. 

For the reasons described above, this AD requires a one-time inspection 

and, depending on findings, adjustment of the torque values of nuts on circuit 

breakers, contactors and terminal blocks. 

Effective Date: 26 May 2011 

EASA Form 110 Page 1/2 
EASA AD No : 2011-0083 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 24 months after the effective date of this AD, inspect and, 

depending on findings, adjust the torque values of nuts on circuit 

breakers, contactors and terminal blocks and do the additional 

corrective actions in accordance with the Accomplishment Instructions 

of Fokker Services SBF50-24-032 or SBF100-24-043, as applicable to 

aeroplane type. 

Concurrent Requirements:

(2) For certain F27 Mark 050 and Mark 0502 aeroplanes, prior to or 

concurrent with the actions required by paragraph (1) of this AD, modify 

the aeroplane in accordance with the accomplishment instructions of 

Fokker Services SBF50-24-031 (only for aeroplanes with serial numbers 

as listed in the SB). Aeroplanes that have already been modified as 

required by EASA AD 2008-0091 are compliant with the modification 

requirement of this paragraph. 

(3) For certain F28 Mark 0070 and Mark 0100 aeroplanes, prior to or 

concurrent with the actions required by paragraph (1) of this AD, modify 

the aeroplane in accordance with the accomplishment instructions of 

Fokker Services SBF100-24-032 (only for aeroplanes with serial 

numbers as listed in the SB). Aeroplanes that have already been 

modified as required by CAA-NL AD (BLA) 1995-089/4 are compliant 

with the modification requirement of this paragraph. 

(4) For certain F28 Mark 0100 aeroplanes, prior to or concurrent with the 

actions required by paragraph (1) of this AD, modify the aeroplane in 

accordance with the accomplishment instructions of Fokker Services 

SBF100-24-041 (only for aeroplanes with serial numbers as listed in the 

SB). Aeroplanes that have already been modified as required by 

EASA AD 2008-0091 are compliant with the modification requirement of 

this paragraph. 

Ref. Publications: Fokker Services SBF50-24-031 dated 29 January 2008. 

Fokker Services SBF50-24-032 dated 10 February 2011. 

Fokker Services SBF100-24-032 dated 12 September 1996, Revision 1 

dated 25 April 1997, or Revision 2 dated 28 July 1997. 

Fokker Services SBF100-24-041 dated 29 January 2008. 

Fokker Services SBF100-24-043 dated 10 February 2011. 

The use of later approved revisions of these documents 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 28 March 2011 as PAD 11-034 for consultation 

until 25 April 2011. The Comment Response Documents can be found 

at http://ad.easa.europa.eu/. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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) 252-627-350; facsimile (31) 252-627-211; 

e-mail: technicalservices.fokkerservices@fokker.com. 

The referenced publication can be downloaded from 

www.myfokkerfleet.com.