EASA

EASA AD No : 2009-0216

AIRWORTHINESS DIRECTIVE

AD No.: 2009-0216

Date: 07 October 2009

Note: This Airworthiness Directive (AD) '5 issued by EASA, acting in accordance with

Regulation (EG) No 21612008 on behalf of the European Community, its Member Slates and

of the European third countries thaI participate in the activities of EASA under Article 66 of

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 01 the ,State of Registry IEC 216/2008, Article 14(4) exemption).

Type Approval Holder's Name:

Fokker Services B.V.

Type/Model designation(s) :

F28 Mark 01 00 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 of the vertical

stabilizer of F28 Mark 0100 ae!roplanes, one of the bolts that connect the

horizontal stabilizer control unit actuator with the dog-links was found broken

(one on the nut side & one on ~he head side). In both occasions, the bolt shaft

was still present in the connection and therefore the horizontal stabilizer

function was not affected. If a single dog-link connection falls, the complete

stabilizer load is taken up by the remaining dog-link connection. Any failed

connection should be detected and corrected at the next scheduled

inspection.

To address and correct this unsafe condition EASA issued AD 2007-0287 that

required a one-lime inspection of the affected bolts, Part Number (PIN)

23233-1, and replacement of failed bolts with serviceable parts. EASA AD

2007-0287 also required the installation of a tie wrap through the lower bolts

of the horizontal stabilizer control unit, to keep the bolt in place in the event of

a bolt head failure.

Recent examination revealed that the bolts failed due to stress corrosion,

attributed to excessive bolt torque. Investigation of the recently failed bolts

showed that the modification as required by AD 2007-0287 is not adequate.

To address the stress corrosio'n, the manufacturer of the bolt, Goodrich, has

introduced a bolt with an improved corrosion protection, PIN 23233-3, throu h

I

I
EASA AD No., 2009-0216

Service Bulletin 23100-27-29.

For the reasons described ab~ve, this EASA AD retains the requirements of

AD 2007-0287, which is superseded, 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 a on~-time inspection of the PIN 23233-1 lower

bolts of the stabilizer cont~ol unit dog-links in accordance with the

Accomplishment InstrUC!i1ns of Fokker SBF100-27-91.

(2) When a failed bolt is found during the inspection as required by

paragraph (1) of this AD, ~efore next flighL, replace the bolt with a

serviceable part and install a tie-wrap PIN MS3367-2-9 through the lower

Required Actlon(s)

bolts of the 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 of this AD, accompiish the

following actions concurrehtly:

(3.1) Remove the tie-wraJ PIN MS3367-2-9 from the lower bolts of the

horizontal stabilizer ~ontrol unit in accordance with the

accomplishment Instructions of Fokker SBF100-27-92,

I

(3.2) Remove the PIN 23233-1 lower boiLs of the horizontal stabilizer

control unit and ins~11 PIN 23233-3 bolts In accordance with the

Instructions ofGoOd~ich S8 23100-27-29.

(4) After 21 April 2012 [30 months after the effective date of this 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 27 April 2009.

Ref. Publications; The use of later approved revilions of these documents is acceptable for

compliance with the requirem~nts of this AD.

Goodrich SB 23100-27-19. I

Goodrich SB 23100-27-29.

,. If requested and appropri1tely substantiated, EASA can approve

Alternative Methods of Cdmpliance for this AD.

I

2. This AD was posted on 27 August 2009 as PAD 09-108 for consultation

until 24 SepLember 2009'INO comments were received during the

consultation period.

3 Enquiries regarding thls,t>;O should 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 of the 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-ma iI: tech nica Iservices. fo kke rservi ces@stark.com

The referenced pUblicatit can be downloaded from

www.myfokkerfleet.com

EASA Form 110