EASA AD No .: 20 14

- 0039

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 14

- 0 0 3 9

Date: 20 February 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 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 [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 aeroplanes

TCDS Number: EASA.A.037

F oreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage

– Tail Section

– Inspection / Repair

Manufacturer(s): Fokker Aircraft B.V.

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

Reason: Service experience has shown that cracks can occur in oblique f rame 67

- 2 in the tail section on aeroplanes with more than 29 000 f light c ycles (FC)

. This condition, if not detected and corrected, can result in an exponential crack growth rate, possibly leading to failure of the oblique f rame 67

- 2 over a certain length and consequent loss of the structural integrity of the tail section of the aeroplane. For the reasons described above, this AD requires a one
- time inspection of the
o blique f rame 67

- 2 for cracks and, depending on findings, accomplishment of a repair.
R epetitive inspection s are planned to be incorporated into a revision of Fokker Services Report SE

- 623
, which is part of the Airworthiness Limitations Section of the Instructions for Continued Airworthiness , for which a separate AD is expected to be published

. Fokker Services All Operators Message AOF100.1 87#02 provides additional information concerning the subject addressed by this AD.

Effective Date: 0 6 March 2014EASA AD No .: 20 14

- 0039

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: (1) F or aeroplanes that, on the effective date of th is AD
, have accumulated or exceeded 29 000 f light c ycles (FC)

, within 500 FC or 12 months , whichever occurs first after the effective date of this AD, inspect the o blique f rame 67

- 2 for cracks in accordance with the Accomplishment Instructions of Fokker Services Service Bulletin (SB) SBF100

- 53

- 1 24

. (2) If, during the inspection as required by paragraph (1) of this AD, a crack is detected, before next flight, repair o blique f rame 67

- 2 in accordance with the Accomplishment Instructions of Fokker Services SBF100

- 53

- 125 Revision 1

.

Ref. Public ations: Fokker Services SBF100

- 53

- 124 dated 23 January 2014

. Fokker Services SBF100

- 53

- 1 25 Revision 1 dated 13 February 201 4

. 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. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments, postponing the public consultation process until after publication

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Executive Directorat e , 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 s can be downloaded from www.myfokkerfleet.com

.