E ASA AD No.: 20 12

- 0 21 9

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 12 - 0 21 9

Date: 19 October 2012

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 EC 7 48 /20 12 , 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): F28 aeroplanes

TCDS Number: EASA.A.037

F oreign AD: Not applicable Supersedure: None



### ATA 53 Fuselage
– Rear Pressure Bulkhead
– Inspection / Repair

Manufacturer(s): Fokker Aircraft B.V. Applicability: F28 Mark 0070 and Mark 0100 aeroplanes, serial numbers as listed in Fokker Services Service Bulletin (SB) SBF100

- 53

- 1 20 dated 1 5 May 2012

. Reason: Three reports have been received of a crack in the rear pressure bulkhead (RPBH) w eb , just below the h orizontal b eam XI between buttock lines BL425L and BL425R, in the cent r e web bay below the pressure relief valves

. This condition, if not detected and corrected, could result in an exponential crack growth rate, possibl y leading to failure of the affected RPBH web , resulting in in

flight decompression of the aeroplane and possible injury to occupants

. A repetitive inspection requirement has been published in issue 10 of Fokker Services ALS Report SE

- 623 under task number 534106

- 00

- 05. The threshold to start this ALS

- task is 30 000 flight cycles (FC). However, it is known that many aeroplanes have already exceeded th is threshold

. For the reasons described above, this AD requires a one - time inspection of the affected RPBH web for cracks and, depending on findings , accomplishment of a repair

. The repair can also be applied at any time as a modification , thereby exempting the aeroplane from (further) repetitive ALS task 534106

- 00

- 05 inspection s

. Effective Date: 0 2 Novem ber 2012E ASA AD No.: 20 12

- 0 21 9

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) Before accumulating 30 000 FC , or within 12 months after the effective date of this AD, whichever occurs later, inspect the affected RPB H web for cracks , either in accordance with Part 1 or in accordance with Part 2 of the Accomplishment Instructions of Fokker Services Service Bulletin (SB) SBF100

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- 1 20

. (2) If, during the inspection as required by paragraph (1) of this AD, either in accordance with Part 1 , or in accordance with Part 2 of the Accomplishment Instructions of Fokker Services SBF100

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- 120 , a crack is detected, before next flight, except as specified in paragraph ( 5 ) of this AD, accomplish a repair in accordance with the i nstructions of Fokker Services SBF100

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- 121. ( 3 ) When the aeroplane is inspect ed , as required by paragrap h (1) of this AD, in accordance with Part 1 of the Accomplishment Instructions of Fokker Services SBF100

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- 120 and no cracks are found, within 12 months after that inspection, inspect the aeroplane in accordance with Part 2 of the Accomplishment Instructions of Fokker Services SBF100

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- 120

. (4) If, during the inspection as required by paragraph (3) of this AD, a ny crack indication is detected, before next flight, accomplish a repair in accordance with the i nstructions of Fokker Services SBF100

- 53

- 121

. ( 5 ) When the aeroplane is inspect ed , as required by paragraph (1) of this AD, in accordance with Part 2 of the Accomplishment Instructions of Fokker Services SBF100

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- 120 and a ny crack indication is detected , an inspection in accordance with Part 1 of the Accomplishment Instructions of SBF100

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- 120 can be accomplished to determine whether repair postponement is allowed

. If , during this inspection , no cracks are found , within 12 months after the inspection where crack indication was first detected, accomplish a repair in accordance with the i nstructions of Fokker Services SBF100

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- 121

. Note: Fokker Services All Operators Message s AOF100.17 6 and AOF100.178 provide additional information concerning the subject addressed by this AD.
Ref. Publications: Fokker Services SBF100

- 53

- 120 dated 1 5 May 2012. Fokker Services SBF100

- 53

- 121 dated 15 May 2012. Fokker Services All Operators Message s AOF100.176 dated 15 May 2012 , and AOF100.178 dated 10 September 2012

. 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 17 September 2012 as PAD 12

- 121 for consultation until 15 October 2012

. N o comments were received during the consultation period. 3. Enquiries 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 content of the requirements in t his 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

.