E ASA AD No.: 20 13

- 0140

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 3
- 01 4 0

Date: 12 Ju ly 201 3

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 21A.3B. In accordance with E C 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 air craft 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.037

F oreign AD: Not applicable

Supersedure: None



### ATA 5 1 Structures General

– Center Wing Rear Spar

– Modification

Manufacturer(s): Fokker Aircraft B.V.

Applicability: F28 Mark 0070 and Mark 0100 aeroplanes, all serial numbers

.

Reason: Two cases have been reported of heavy aileron control caused by aileron cables stuck in a clump of ice in the wheel bay

. Investigation results revealed that , i n case of water accumulation on the top of the center wing torsion box inside the cabin (zones 171 and 172), the water drains through the existing drain holes/gaps in the web plates on top of the center wing rear spar . The water could then accumulate i n the area where the aileron control cables are situated . With the freezing temperatures normally encountered during flight , ice accretion could occur near or even on the aileron control cables. This condition, if not corrected, could result in reduced control of the aeroplane.
For the reasons described above, this AD requires the installation of drain tubes on the center wing rear spar

.

Effective Date: 26 July 2013E ASA AD No.: 20 13

- 0140

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. Within 36 months after the effective date of this AD, install w ater d rain t ubes o n the c enter w ing r ear s par in accordance with the i nstructions of Fokker Services Service Bulletin (SB) SBF 100

- 51

- 0 21

. Note: More information on this subject can be found in Fokker Services All Operators Message AOF100.1 84

. Ref. Publications: Fokker Services SBF100

- 5 1

- 021 dated 23 April 201 3

. Fokker Services All Operators Message AOF100. 184 dated 23 April 201 3. The use of later approved revisions of th ese 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 12 June 2013 as PAD 13

- 074 for consultation until 10 July 2013. No comments were received during the consultation period

. 3. Enqui ries 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 conte nt of the requirements in this AD, please contact: Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL, Hoofddorp, The Netherlands; telephone +31

- 88

- 6280

- 350; facsimile +31

- 88

- 6280

- 111; E

- mail: technicalservices@fokker.com

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

.