EASA AD No.: 2012-0219

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0219

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 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 aircraft to 

which an AD applies, except in accordance with the requirements 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

Foreign 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) SBF100-53-120 dated 15 May 2012.

Reason: Three reports have been received of a crack in the rear pressure bulkhead

(RPBH) web, just below the horizontal beam XI between buttock lines BL425L and

BL425R, in the centre web bay below the pressure relief valves.

This condition, if not detected and corrected, could result in an exponential crack 

growth rate, possibly leading to failure of the affected RPBH web, resulting in inflight 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 this 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

inspections.

Effective Date: 02 November 2012
EASA AD No.: 2012-0219

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Required Action(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 RPBH 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) 

SBF100-53-120.

(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 SBF100-53-120, a crack is detected, before 

next flight, except as specified in paragraph (5) of this AD, accomplish a 

repair in accordance with the instructions of Fokker Services SBF100-53-121.

(3) When the aeroplane is inspected, as required by paragraph (1) of this AD, in 

accordance with Part 1 of the Accomplishment Instructions of Fokker 

Services SBF100-53-120 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 SBF100-53-120.

(4) If, during the inspection as required by paragraph (3) of this AD, any crack

indication is detected, before next flight, accomplish a repair in accordance 

with the instructions of Fokker Services SBF100-53-121.

(5) When the aeroplane is inspected, as required by paragraph (1) of this AD, in 

accordance with Part 2 of the Accomplishment Instructions of Fokker 

Services SBF100-53-120 and any crack indication is detected, an inspection 

in accordance with Part 1 of the Accomplishment Instructions of SBF100-53-

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 instructions of Fokker Services SBF100-53-121.

Note: Fokker Services All Operators Messages AOF100.176 and AOF100.178 

provide additional information concerning the subject addressed by this AD.

Ref. Publications: Fokker Services SBF100-53-120 dated 15 May 2012.

Fokker Services SBF100-53-121 dated 15 May 2012.

Fokker Services All Operators Messages AOF100.176 dated 15 May 2012, and 

AOF100.178 dated 10 September 2012.

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. This AD was posted on 17 September 2012 as PAD 12-121 for consultation 

until 15 October 2012. No 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 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 can be downloaded from www.myfokkerfleet.com.