EASA AD No.: 2009-0269R1 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0269R1 

Date: 11 March 2010 

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 EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 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 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

Fokker Services B.V.

Type/Model designation(s) : 

F28 Mark 0100 aeroplanes 

TCDS Number : EASA.A.037 

Foreign AD : Not applicable 

Revision : This AD revises and replaces EASA AD 2009-0269 dated 17 December 2009. 

ATA 32 Landing Gear – Main Landing Gear (MLG) – Modification / 

Replacement 

Manufacturer(s): Fokker Aircraft B.V. 

Applicability: 

F28 Mark 0100 aeroplanes, all serial numbers, if Messier-Dowty (formerly 

Dowty-Rotol, Dowty Aerospace Gloucester) MLG units with Part Number 

(P/N) 201072011, P/N 201072012, P/N 201072013, P/N 201072014, P/N 

201072015 or P/N 201072016 are installed. 

Reason: 

Since introduction of the F28 Mark 0100 aeroplane into airline service, there 

have been a number of occurrences with Messier-Dowty MLG units where 

the main fitting failed, due to fatigue cracking in the area of the filler and 

bleeder holes, and occurrences where the sliding member failed, due to 

fatigue cracking at the area of chrome run-out/lower radius of the sliding tube 

portion of the sliding member. 

Investigation has revealed that the most probable cause of both the main 

fitting and sliding member cracks is high compressive stress during braking at 

higher deceleration levels outside the regular fatigue load spectrum. Starting 

at deceleration stress levels somewhat below limit load, the high compressive 

stress locally exceeds the elasticity limit of the material, leaving a residual 

tensile stress at release of the heavy braking load. Subsequently, this local 

residual tensile stress results in a negative effect on the fatigue life of the 

component. 

This condition, if not detected and corrected, could lead to failure of the MLG, 

possibly resulting in loss of control of the aeroplane during the landing rollout. To address this unsafe condition, the Civil Aviation Authority of the 
EASA AD No.: 2009-0269R1 

EASA Form 110 Page 2/3 

Netherlands (CAA-NL) issued AD NL-2005-012 (EASA approval 2005-6363) 

to require repetitive inspections of the sliding member (Fokker Services 

SBF100-32-144) and AD NL-2006-003 (EASA approval 2006-0041) to 

require repetitive inspections of the main fitting (Fokker Services SBF100-32-

146). Messier-Dowty has now developed a modification, resulting in a 

strengthened sliding member and a strengthened main fitting, which is the 

terminating action for these repetitive inspections. 

For the reasons described above, this AD requires the modification and reidentification of the affected MLG units, or replacement of the affected MLG 

units with modified units. 

This AD has been revised to correct paragraph (3) and to amend paragraph 

(5) to state that modification of an aeroplane as required by paragraph (1) of 

this AD also constitutes terminating action for the actions required by CAA-NL 

AD (BLA) 2002-115/2 dated October 8, 2004. 

Effective Date: 

Revision 1 : 11 March 2010 

Original issue : 31 December 2009 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously. 

(1) At the next MLG overhaul or within 48 months, whichever occurs first 

after the effective date of the original issue of this AD, modify the 

aeroplane by accomplishing the actions of either paragraph (1.1) or (1.2) 

of this AD: 

(1.1) Replace each affected MLG unit with a MLG unit having P/N 

201072017, P/N 201072019 or P/N 201072021 (LH), and P/N 

201072018, P/N 201072020 or P/N 201072022 (RH), in 

accordance with the Accomplishment Instructions of Fokker 

Services SBF100-32-155. 

(1.2) Modify and re-identify each affected MLG unit in accordance with 

the Accomplishment Instructions of Messier-Dowty SB 

F100-32-112. 

(2) After modification of an aeroplane as required by paragraph (1) of this 

AD, do not install a P/N 201072011, P/N 201072012, P/N 201072013, 

P/N 201072014, P/N 201072015 or P/N 201072016 MLG unit on that 

aeroplane. 

(3) Prior to returning the aeroplane to service after modification as required 

by paragraph (1) of this AD, remove the Airplane Flight Manual 

amendment and placard that were installed as required by CAA-NL BLA 

2002-115 (Fokker Services SBF100-32-137). 

(4) Before or concurrent with the modification of an aeroplane as required by 

paragraph (1) of this AD, accomplish the following actions: 

(4.1) Introduce the torque link spacer with changed outer diameter in 

accordance with the Accomplishment Instructions of Fokker 

Services SBF100-32-097. 

(4.2) Remove, if installed, the water spray deflectors in accordance with 

the Accomplishment Instructions of Fokker Services 

SBF100-32-132. 

(4.3) Replace all P/N AE70690E, P/N AE70691E, P/N AE99111E and 

P/N AE99119E brake quick-disconnect couplings with improved 

units in accordance with Part 2 of the Accomplishment Instructions 

of Fokker Services SBF100-32-156. EASA AD 2009-0176 also 

requires this modification, the compliance time of which expires on 

20 August 2011 for aeroplanes registered in Europe. 

(5) Modification of an aeroplane as required by paragraph (1) of this AD 

constitutes terminating action for the requirements of the following ADs: 
EASA AD No.: 2009-0269R1 

EASA Form 110 Page 3/3 

 - CAA-NL AD (BLA) 93-108/3 dated April 29, 1994. 

 - CAA-NL AD (BLA) 1996-133/2 dated January 31, 1997. 

 - CAA-NL AD (BLA) 2002-115/2 dated October 8, 2004. 

 - CAA-NL AD NL-2005-012 (EASA 2005-6363) dated October 17, 2005. 

 - CAA-NL AD NL-2006-003 (EASA 2006-0041) dated February 7, 2006. 

(6) Modification of an aeroplane as required by paragraph (1) of this AD 

constitutes compliance with the following ADs: 

 - CAA-NL AD (BLA) 90-022/2 dated June 29, 1990. 

 - CAA-NL AD (BLA) 2003-040 dated March 31, 2003 and its Correction 

issued May 14, 2003. 

(7) Compliance with the following ADs is required prior to or concurrent with 

modification of an aeroplane as required by paragraph (1) of this AD: 

 - CAA-NL AD (BLA) 1999-138 dated October 29, 1999, the compliance 

time of which expired on 20 November 2001 for aeroplanes registered in 

Europe. 

 - CAA-NL AD NL-2005-008 (EASA 2005-6044) dated June 30, 2005, the 

compliance time of which expired on 15 July 2006 for aeroplanes 

registered in Europe. 

 - CAA-NL AD NL-2007-001 (EASA 2007-0054) dated February 26, 2007, 

the compliance time of which expired on 01 September 2009 for 

aeroplanes registered in Europe. 

Ref. Publications: 

Fokker Services SBF100-32-155 dated 23 July 2009. 

Messier-Dowty Service Bulletin SB F100-32-112 dated 17 July 2009. 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 

Remarks:

1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The original issue of this AD was posted on 23 October 2009 as PAD 

09-128 for consultation until 20 November. The Comment Response 

Document can be found at http://ad.easa.europa.eu/. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail ADs@easa.europa.eu. 

4. For any question concerning the technical aspects of the requirements in 

this AD, please contact: 

Fokker Services B.V., 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: technicalservices.fokkerservices@stork.com 

The referenced publication can be downloaded from 

www.myfokkerfleet.com