EASA AD No.: 2015

- 0024

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2015
- 0 0 24

Date: 19 February 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 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 [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) exempt ion]. 

### 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 5 3 Fuselage

– Skin Connection A ngle and P ressure B ulkhead

– 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 pressure bulkhead webplate and skin connection angle on the right hand ( RH ) side at station 14911 (station 12447 for F28 Mark 0070) at stringer 67 of fuselage section 2, before reaching the existing threshold for inspection per ALS task 533016

- 00

- 03 (F28 Mark 0100) or task 533016

- 01

- 03 (F28 Mark 0070)

. Any cracks in this area are not visible from the outside (covered by fairing) until they reach a critical length. This condition, if not detected and corrected, could lead to sudden in

- flight decompression of the aeroplane , possibly resulting in injury to occupants

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

- 5 3

- 128 , which provides inspection instructions to detect any crack in the affected area

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

- time ins pection of the affected pressure bulkhead webplate and skin connection angle , 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 lower the current ALS task threshold , if justified by the inspection results

.
Effective Date: 05 March 2015EASA AD No.: 2015

- 0024

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 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 the compliance time as specified in Table 1 of this AD, as applicable, inspect the pressure bulkhead webplate and skin connection angle on the RH side at station 14911 ( for F28 Mark 0100), or station 12447 ( for F28 Mark 0070) at stringer 67 of fusel age section 2, in accordance with the Accomplishment Instructions of Fokker Services SBF100

- 53

- 12 8.

Table 1

– Inspection Flight c ycles (FC) accumulated on the effective date of this AD Compliance Time

Less than 40 000 FC (see Note) Before exceeding 40 750 FC, or
w ithin 2 000 FC , whichever occurs first after the effective date of this AD

40 000 FC or more W ithin 750 FC after the effective date of this AD Note: This AD does not require action for aeroplanes that, on the effective date of this AD, have accu mulated less than 30 000 FC

. (2) If, during the inspection as required by paragraph (1) of this AD, a ny crack i s found in the skin connection angle, but none in the pressure bulkhead webplate , within 4 000 FC after crack detection , repair the skin connection angle in accordance with the instructions of Fokker Services SBF100

- 53

- 129

. (3) If, during the inspection as required by paragraph (1) of this AD, any crack is found in the pressure bulkhead webplate which does not reach the vertical stiffener (BL800R) , b efore next flight, stop

- drill the crack, and , w ithin 2 000 FC after crack detection , re - inspect the area in accordance with the Accomplishment Instructions of Fokker Services SBF100

- 53

- 128. (4) If, du ring the inspection as required by paragraph ( 3 ) of this AD, no crack growth is found beyond the stop drill hole, within 4 000 FC after crack detection, repair the pressure bulkhead webplate in accordance with approved repair instructions provided by Fokker Services SBF100

- 53

- 129. (5) If, during the inspection as required by paragraph ( 3 ) of this AD, any crack growth is found beyond the stop drill hole, before next flight, repair the pressure bulkhead webplate in accordance with the instructions of Fokker Services SBF100

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- 129 , or contact Fokker Services for approved repair instructions and , within the compliance time(s) specified in those instructions, accomplish the repair accordingly

. (6) If, during the inspection as required by paragraph (1) of this AD, any crack is found in the pressure bulkhead webplate which reaches the vertical stiffener (BL800R) , before next flight, repair the pressure bulkhead webplate in accordance with the instructions of Fokker Services SBF100

- 53

- 129 , or contact Fokker Services for approved repair instructions and, within the compliance time(s) specified in those instructions, accomplish the repair accordingly

. (7) Within 30 days after the inspection as required by paragraph (1) of this AD, report the results (including no findings) to Fokker Services in accordance with the i nstructions of Fokker Services SBF100

- 53

- 128

. Ref. Publications: Fokker Services SBF100

- 5 3

- 12 8 original issue dated 12 Novem ber 2014. Fokker Services SBF100

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- 129 original issue dated 16 February 2015. The use of later approved revisions of th e s e document s is acceptable for compliance with the requirements of this AD. More information on this subject can be found in Fokker Services All Operators Message AOF100.193 and AOF100.193#02

.EASA AD No.: 2015

- 0024

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 1 0 December 201 4 as PAD 1 4

- 17 1 for consultation until 07 January 201 5

. 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 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 s can be downloaded from www.myfokkerfleet.com

.