EASA AD No.: 20 1 5

- 0091

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 5

- 0 0 9 1

Date: 26 May 2015

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 EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requ irements of that AD, unless otherwise specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemp tion].


### 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 2 7 Flight Controls

– Elevator T ension C ontrol R egulator

– Inspection

Manufacturer(s): Fokker Aircraft B.V.

Applicability: F28 Mark 0 070 and Mark 0 100 aeroplanes

, all serial numbers

.

Reason: During the accomplishment of the taxi

- out checklist on a n F28 Mark 0100 aeroplane , the flight crew noticed that the elevator movement was part ial ly obstructed

. The subsequent investigation revealed that this was due to rotation of the flight control lock adjuster bracket, which had come loose from the elevator tension control regulator

. T wo of the three attachment bolts were found broken

, and two nuts were missin g. Although no root cause could be identified for the absence of these nuts , the y are considered as the main contributor to the occurrence

. This condition

, if not detected and correct ed

, c ould lead to jamming of the elevator mechanism , possibly resulting in reduced control of the aeroplane

. To address this potential unsafe condition

, Fokker Services published Service Bulletin (SB) SBF100

- 2 7

- 095 which provides instructions to detect and correct any discrepancies , and to re

- install missing or broken parts (if any)

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

- time ins pection of the elevator tension control regulator and, d epending on findings

, accomplishment of applicable corrective action(s). More information on this subject can be found in Fokker Services All Operators Message AOF100.19 8

.

Effective Date: 09 June 2015EASA AD No.: 20 1 5

- 0091

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) At the next scheduled opening of access panels 346AB or 346BL after the effective date of this AD , but no later than 5 000 flight hours after the effective date of this AD, inspect the elevator tension control regulator in accordance with the Accomplishment Instructions of Fokker Services SBF 100

- 2 7

- 0 95

. (2) If, during the inspection as required by paragraph (1) of this AD

, the flight control lock adjuster bracket is found loose

, or any bracket attachment bolt is found broken

, or any nut is missing, before next flight, accomplish the applicable corrective action(s ) in accordance with the Accomplishment Instructions of Fokker Services SBF100

- 2 7

- 095

. (3) Within 30 days after finding any discrepancy during the inspection as required by paragraph (1) of this AD, report the findings to Fokker Services B.V. , address deta ils in the Remarks section of this AD.

Ref. Publications: Fokker Services SBF100

- 2 7

- 0 95 original issue dated 22 April 2015

. The use of later approved revisions of th is 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 23 April 2015 as PAD 15

- 048 for consultation until 21 May 2015. No comments were received during the consultation period.

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 content 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: technicalservi ces@fokker.com

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

.