E ASA AD No.: 20 14

- 0271

TE. CAP.0011 0

- 00 4 © 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 - 0271

Date: 12 December 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 operate an air craft to which an AD applies, except in accordance with the requ irements 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): F2 8 aeroplanes

TCDS Number: EASA.A.03 7

F oreign AD: Not applicable
Supersedure: No ne



### ATA 57 Wings

– Trailing Edge Rib at Wing Station 8700

– Inspection

Manufacturer(s): Fokker Aircraft B.V.
Applicability: F28 Mark 0070 and Mark 0100 aeroplanes, all serial numbers

. Reason: Service experience with the Fokker 100 type design has shown that cracking can occur in the secondary structure of the wing at station 8700 , rib Part Number (P/N ) D15445

- 013/

- 014 ( or lower dash number) in the trailing edge section. T he hydraulic actuator assembly, hydraulic lines, the cable pulleys, the anti

- upfloat quadrant and the associated mechanical linkages including flutter dampers are all positioned in the affected area , between wing stations 8200 and 9 270

. This condition , if not detected and correct ed , could lead to failure of the affected rib, possibly resulting in reduced control of the aeroplane

. To address this potential unsafe condition , Fokker Services published Service Bulletin (SB) SBF100

- 57

- 048 , which provides inspection instructions to detect any cracks in the affected area

. For the reasons described above, this AD requires a one

- time ins pection of the t railing edge rib at wing station 8700 and, d epending on findings , accomplishment of applicable corrective action(s). T his AD is considered to be an interim action and further AD action may follow , possibly to introduce new ALS tasks , if justified by the inspection results

. Effective Date: 29 December 2014E ASA AD No.: 20 14

- 0271

TE. CAP.0011 0

- 00 4 © 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 12 months a fter the effective date of this AD, inspect the trailing edge rib at wing station 8700 in accordance with the Accomplishment Instructions of Fokker Services SBF 100

- 57

- 048. (2) If, during the inspection as required by paragraph (1) of this AD , a ny crack i s found , before next flight, contact Fokker Services for approved repair instructions an d accomplish those instructions accordingly.
Ref. Publications: Fokker Services SBF100

- 57

- 048 original issue dated 27 October 2014. The use of later approved revisions of th is document is acceptable for compliance with the requirements of this AD. More information on this subject can be found in Fokker Services All Operators Message AOF100.192.
Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 04 November 2014 as PAD 14

- 163 for consultation until 02 December 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification 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; 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

.