EASA

EASA AD No .. 2009-0221

AIRWORTHINESS DIRECTIVE

AD No.: 2009-0221

Date: 14 October 2009

Note: This Airworthiness Directive (AD) is issued by EASA. acting ill accordance with

Regulation lEG) No 216f2008 on behalf of the European Community, its Member Stales 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 170212003, Pan 21A3B_ In accordance with EC 204212003 Annel{ I. Part MA301. the

continuing airworthiness of an aircraft shall be ensured by accomplishing ar'\y appliq,ble ADs. Consequently, no person m<lYoperate

an aircraft 10which an AD applies, except in accordance with the requirements of that AD, unless otherwise specif>ed by the Agency

[EG 204212003 Annex I, Part M.A.303) or agreed with the Authority of the Slale of Registry lEG 21612008, Article 14(4) exemptjonl.

Type Approval Holder's Name:

Fokker Services B.v.

Type/Model designation(s) :

F28 Mark 0070 and Mark 0100 aeroplanes

TCDS Number:

Foreign AD:

Supersedure:

ATA32

Manufacturer(s):

Applicabillly:

Reason:

Effective Date:

EASA Form 110

EASA.A.037

Not applicable

None

landing Gear - Main landing Gear (MlG) Piston - Inspection I

Replacement

Fokker Aircraft B.V.

F28 Mark 0070 and Mark 0100 aeroplanes, all serial numbers, if equipped

with Goodrich (formerly Menasco, Colt Industries) MLG units, Part Number

(PIN) 41050·7, PIN 41050·8, PIN 41050·9, PIN 41050·10, PIN 41050·11 ,

PIN 41050-12, PIN 41050-13, PIN 41050-14, PIN 41050-15, PIN 41050·16,

PIN 41060·1, PIN 41060-2, PIN 41060-3, PIN 41060·4, PIN 41060-5 or PIN

41050·6.

During a normal walkaround check on a F28 Mark 0100 aeroplane, a large

crack was discovered in the lower porlion of the right (RH) MLG piston. The

affected MlG unit had accumulated 7 909 flight cycles (FC) at the time of

detection. The piston has been senl to Goodrich, the landing gear

manufacturer, for detailed investigation,

This condition, if nol detecled and corrected, could lead to MlG failure,

possibly resulting in loss of control of the aeroplane during the landing roll-out.

For the reasons described above, this AD requires a one-lime detailed visual

inspection of the MLG pistons, :the replacement of any MLG pistons on which

cracks are detected, and the reporting of all findings 10 the aeroplane TC

holder. The inspection results, in combination with the findings of the

crack/metallurgical investigation of the cracked piston by Goodrich, will be

used to determine the necessity of additional and/or more detailed

inspections, or any other corrective action. This AD is considered an interim

measure and further action is likely to follow_

28 October 2009

Page 112
EASA AD No_: 2009-0221

Required as indicated, unless accomplished previously:

(1 ) Within 30 days after the effective date of this AD, accomplish a detailed

visual inspection of the MLG pistons for cracks in accordance with the

Accomplishment Instructions of Fokker Services Service Bulletin (S8)

SBF100-32-158 and Goodrich SB 41000-32-28 Revision 1.

Required Action(s) (2) If a cracked MLG piston is found during the inspection as required by

and Compliance paragraph (1) of this AD, before next flight, replace the affected piston

Time(s): with a serviceable part in accordance with the Accomplishment

Instructions of Fokker Services SBF100-32-158.

(3) Within 10 days after the inspection as required by paragraph (1) of this

AD, report the inspection results (including no findings) to Fokker

Services by using the Questionnaire attached to Fokker Services

SBF100-32-158.

Fokker Services SBF1 00-32-158 dated 02 October 2009.

Ref. Publications: The use of later approved revisions of this document is acceptable for

compliance with the requirements of this AD.

Goodlich Service Bulletin 41000-32-28 Revision 1 dated 29 September 2009.

1. If requested and appropriately substantiated, EASA can approve

Alternative Methods of Compliance for this AD.

2. The required actions and the risk allowance have granted the issuance of

a Final AD with Request for Comments, postponing the public

consultation process after publication.

3. Inquiries regarding this ADlshould be referred to the Airworthiness

Directives, Safety Management & Research Section, Certification

Remarks: 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.Y., Technical Services Dept., P.O.Box 231,

2150 AE Nieuw-Vennep, The Netherlands;

telephone (31) 252-627-350; facsimile (31) 252-627-211;

E-mail: tech nica lservices. fokkerservices@stork.com

The referenced publication can be downloaded from

www.myfokkerfleet.com

EASA Form 110 Page 212