## EASA EASAAD No:2009-0216 

## AIRWORTHINESS DIRECTIVE
AD No.: 2009-0216

Date: 07October 2009
Note: This AirworthinessDirective(AD) '5 issued by EASA, acting in accordancewith Regulation (EG) No 21612008 on behalf of the European Community, its Member Slates and ofthe Europeanthird countriesthaI participateinthe activitiesof EASAunderArticle 66of that Regulation. This AD is issued in accordance with EC 170212003, Part 21A.JB. In aceordar'lce with EC 204212003 Annex I, Part MA301, the continuing airworthiness of an "irerafl 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 requirell'enls of Ihat AD, unless otherwise specified by the Agency rEC 204212003 Annex I, Pi:lrt M.A.J03) or agreed with the Authority 01the ,State of Registry IEC 216/2008, Article 14(4) exemption). 

### TypeApproval Holder's Name: Fokker Services B.V. Type/Model designation(s) : F28 Mark 0100 aeroplanes

P'g' 1/

# 1 TeDS Number: Foreign AD: Supersedure:



### ATA 27

Manufacturer(s): Applicability:

Reason:

EASA Form 110 EASA A.03?
Not applicable
This AD supersedes EASA AD 2007-0287 dated 15 November 2007.


### Flight,Controls
- Horizontal Stabilizer Control Unit Dog-Link Attachment
- Modification

Fokker Aircraft B.V.
F28 Mark 0100 aeroplanes, all serial numbers_
Two reports have been receiv~d where, during inspection ofthe vertical stabilizer of F28 Mark 0100 ae!roplanes, one ofthe bolts that connect the horizontal stabilizer control unit actuator with the dog-links was found broken (one on the nut side &one on ~hehead side). Inboth occasions, the bolt shaft was still present inthe connection and therefore the horizontal stabilizer function was not affected. Ifasingle dog-link connection falls, the complete stabilizer load istaken up bythe remaining dog-link connection. Any failed connection should be detected and corrected atthe next scheduled inspection. To address and correct this unsafe condition EASA issued AD 2007-0287 that required aone-lime inspection ofthe affected bolts, Part Number (PIN) 23233-1, and replacement offailed bolts with serviceable parts. EASA AD 2007-0287 also required the installation of atiewrap through the lower bolts ofthe horizontal stabilizer control unit, to keep the bolt in place inthe event of abolt head failure. Recent examination revealed that the bolts failed due to stress corrosion, attributed to excessive bolt torque. Investigation ofthe recently failed bolts showed that the modification as required byAD 2007-0287 is not adequate. To address the stress corrosio'n, the manufacturer ofthe bolt, Goodrich, has introduced abolt with an improved corrosion protection, PIN 23233-3, throu h 

### I IEASA AD No., 2009-0216 Service Bulletin 23100-27-29. Forthe reasons described ab~ve, this EASA AD retains the requirements of AD 2007-0287, which issuperseded, and adds the requirement to replace the affected PIN 23233-1 bolts with improved bolts. Concurrently, the tie-wrap must be removed.
, Effective Date: 21 October 2009 

### I Required as indicated, unless FccomPlished previously. Re-statement of EASA AD 2007·0287 requirements; (1) Within 6 months after 29 ~ovember 2007 [the effective date of EASA AD 2007-0287], perform aon~-time inspection ofthe PIN 23233-1 lower bolts ofthe stabilizer cont~ol unit dog-links in accordance with the Accomplishment InstrUC!i1ns of Fokker SBF100-27-91. (2) When afailed bolt isfound during the inspection as required by paragraph (1) ofthis AD, ~efore next flighL, replace the bolt with a serviceable part and install atie-wrap PIN MS3367-2-9 through the lower Required Actlon(s) bolts ofthe stabilizer contrel unit in accordance with the instructions of Goodrich (formerly Menas'co) SB 23100-27-19. and Compliance New actions required by thiJ AD: Time(s}: (3) Within 30 months after thJ effective date ofthis AD, accompiish the following actions concurrehtly: (3.1) Remove the tie-wraJ PIN MS3367-2-9 from the lower bolts ofthe horizontal stabilizer ~ontrol unit in accordance with the accomplishment Instructions of Fokker SBF100-27-92,



### I (3.2) Remove the PIN 23233-1 lower boiLsofthe horizontal stabilizer control unit and ins~11 PIN 23233-3 bolts Inaccordance with the Instructions ofGoOd~ich S8 23100-27-29. (4) After 21 April 2012 [30 months after the effective date ofthis AD], do not install bolt PIN 23233-1 o~tie-wrap PIN MS3367-2~9 on any aeroplane. Fokker Services SBF100-27-0~1 dated 31 August 2007. Fokker Services SBF100-27-092 dated 27April 2009. Ref. Publications; The use of later approved revilions ofthese documents isacceptable for compliance with the requirem~nts of this AD. Goodrich SB 23100-27-19. I Goodrich SB 23100-27-29. 

# ,. Ifrequested and appropri1tely substantiated, EASA can approve Alternative Methods of Cdmpliance for this AD. 

### I 2. This AD was posted on 27August 2009 as PAD 09-108 for consultation until 24 SepLember 2009'INO comments were received during the consultation period. 

### 3 Enquiries regarding thls,t>;Oshould be referred to the Airworthiness Directives, Safety Manag4ment & Research Section, Certification Remarks: Directorate, EASA. E-maii ADs@easa,europa.eu. 

### 4. For any question concerning the technical content ofthe requirements in this AD, piease contact: 

### I Fokker Services BV., Te4hnical Services Oept., P,O.Box 231. 2150 AE Nieuw-Vennep, The Netherlands; telephone (31) 252-627-3pO; facsimile (31) 252-627·211; e-maiI:technicaIservices. fokkerservices@stark.com The referenced pUblicatit can be downloaded from www.myfokkerfleet.com

EASA Form 110