## EASA EASA AD No
.. 2009-0221 

## AIRWORTHINESS DIRECTIVE AD No.: 2009-0221

Date: 14October 2009 Note: This Airworthiness Directive (AD) is issued by EASA. acting ill accordancewith Regulation lEG) No 216f2008 on behalf ofthe European Community, its Member Stales and ofthe European third countries that participate in theactivities of EASAunderArticle 66ofthat Regulation. This AD is issued in accordance with EC 170212003, Pan 21A3B_ In accordance with EC 204212003Annel{ I. Part MA301. the continuing airworthiness ofanaircraft shall beensured byaccomplishing ar'\yappliq,ble ADs. Consequently, noperson m<lYoperate anaircraft 10which anAD applies, except in accordance with the requirements ofthatAD, unless otherwise specif>edbytheAgency [EG204212003Annex I, PartM.A.303)oragreed withtheAuthority ofthe Slale of Registry lEG21612008,Article 14(4)exemptjonl. 

### TypeApproval 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, ifequipped 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 inthe 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 ofthe aeroplane during the landing roll-out. For the reasons described above, this AD requires aone-lime detailed visual inspection ofthe MLG pistons, :the replacement of any MLG pistons on which cracks are detected, and the reporting of all findings 10the aeroplane TC holder. The inspection results, in combination with the findings ofthe crack/metallurgical investigation ofthe 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 112EASA AD No_:2009-0221 Required as indicated, unless accomplished previously: 

### (1) Within 30 days after the effective date ofthis AD, accomplish adetailed visual inspection ofthe 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) Ifa cracked MLG piston is found during the inspection as required by and Compliance paragraph (1) ofthis 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) ofthis 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 ofthis document isacceptable for compliance with the requirements ofthis AD. Goodlich Service Bulletin 41000-32-28 Revision 1 dated 29 September 2009. 

### 1. Ifrequested 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 ofthe 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 nicalservices. fokkerservices@stork.com The referenced publication can be downloaded from www.myfokkerfleet.com

EASA Form 110 Page 212