EASA AD No.: 2015-0024

TE.CAP.00110-004 © 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.: 2015-0024

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 aircraft to 

which an AD applies, except in accordance with the requirements 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) 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 – Skin Connection Angle and Pressure Bulkhead –

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) SBF100-53-128, which provides inspection instructions to detect any 

crack in the affected area.

For the reasons described above, this AD requires a one-time inspection of the 

affected pressure bulkhead webplate and skin connection angle, and, depending 

on findings, accomplishment of applicable corrective action(s).

This 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 2015
EASA AD No.: 2015-0024

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(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 fuselage section 2, in accordance with the 

Accomplishment Instructions of Fokker Services SBF100-53-128.

Table 1 – Inspection

Flight cycles (FC) accumulated 

on the effective date of this AD Compliance Time

Less than 40 000 FC (see Note)

Before exceeding 40 750 FC, or 

within 2 000 FC, whichever occurs 

first after the effective date of this AD

40 000 FC or more Within 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 accumulated less than 30 000 FC.

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

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), before next flight, stop-drill the crack, and, within 2 000 FC

after crack detection, re-inspect the area in accordance with the 

Accomplishment Instructions of Fokker Services SBF100-53-128.

(4) If, during 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 SBF100-53-129, 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 instructions of Fokker Services SBF100-53-128.

Ref. Publications: Fokker Services SBF100-53-128 original issue dated 12 November 2014.

Fokker Services SBF100-53-129 original issue dated 16 February 2015.

The use of later approved revisions of these documents 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.00110-004 © 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 10 December 2014 as PAD 14-171 for consultation 

until 07 January 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; Fax +31-88-6280-111;

E-mail: technicalservices@fokker.com. The referenced publications can be 

downloaded from www.myfokkerfleet.com.