EASA AD No.: 2009-0176 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0176 

Date: 06 August 2009 

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 0070 and Mark 0100 aeroplanes 

TCDS Number : EASA.A.037 

Foreign AD : Not applicable 

Supersedure : None 

ATA 32 Landing Gear – Brake Quick Disconnect Couplings – Inspection / 

Replacement 

Manufacturer(s): Fokker Aircraft B.V. 

Applicability: 

F28 Mark 0070 and Mark 0100 aeroplanes, all serial numbers, if Part Number 

(P/N) AE70690E, P/N AE70691E, P/N AE99111E or P/N AE99119E brake 

Quick-Disconnect (QD) couplings are installed. 

Reason: 

During 1995, several reports were received of brake QD couplings loosened 

and/or disconnected during operation. In a few cases, residual brake pressure 

was trapped in the affected brake, causing asymmetric braking and/or 

resulting in hot brakes. Loosened couplings may cause a hydraulic leak with 

the risk of a brake fire. Investigation revealed that the installation of the brake 

QD couplings must be done with care and that the locking teeth on the light 

alloy sleeve are prone to wear. The Fokker 70/100 Aircraft Maintenance 

Manual (AMM) has been revised to include additional information to ensure 

correct removal and installation of the couplings. 

In 1997, Fokker Services issued SBF100-32-106, recommending the 

introduction of QD couplings with corrosion resistant steel (CRES) sleeves 

that would prevent excessive wear of the locking teeth on the light alloy 

sleeve. In response to more reported cases of loosened QD couplings 

resulting in brake problems, further improved QD couplings were introduced 

in 2001 through SBF100-32-127. These couplings increase the reliability of 

the brake system. 

Recently, a brake fire was reported which was caused by a ruptured brake 

piston. The fire was quickly extinguished but caused damage to the paint and 

hydraulic/electrical harness and its components. Detailed investigation 
EASA AD No.: 2009-0176 

EASA Form 110 Page 2/3 

showed that a hydraulic lock must have been present close to the affected 

brake creating enough internal pressure to rupture the piston. The most 

probable scenario for the hydraulic lock is a loosened (not necessarily 

disconnected) brake QD coupling. Further investigation of the service 

experience files at Fokker Services showed that more brake fires have 

occurred on aeroplanes in a pre-mod SBF100-32-127 configuration. 

In order to reduce the probability of a fluid fire as described in CS 25.863, 

additional action is deemed necessary. 

For the reasons described above, this AD requires repetitive inspections of 

the affected brake QD couplings and replacement of the QD couplings with 

improved units. Installation of the improved QD couplings terminates the 

repetitive inspections requirements. 

Effective Date: 20 August 2009 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously. 

(1) Within 6 months after the effective date of this AD, inspect the brake QD 

couplings in accordance with Part 1 of the Accomplishment Instructions 

of Fokker Services SBF100-32-156 (the SB). 

(2) Thereafter, at intervals determined by the amount of wear found, as 

defined in the SB, repeat the inspection in accordance with Part 1 of the 

Accomplishment Instructions of the SB. 

(3) If, during any inspection as required by paragraph (1) or (2) of this AD, 

the wear found on any QD coupling exceeds the definition as specified in 

the SB, before next flight, replace the affected QD coupling with an 

improved unit with P/N AE73059E or P/N AE73091E, as applicable, in 

accordance with Part 2 of the Accomplishment Instructions of the SB. 

(4) Within 24 months after the effective date of this AD, replace all remaining 

P/N AE70690E, P/N AE70691E, P/N AE99111E and P/N AE99119E 

brake QD couplings with the improved units in accordance with Part 2 of 

the Accomplishment Instructions of the SB. 

(5) Modification of an aeroplane by installation of improved QD couplings 

P/N AE73059E and P/N AE73091E at all locations terminates the 

repetitive inspection requirements of this AD for that aeroplane. Previous 

replacement of the QD couplings on an aeroplane at all locations in 

accordance with Fokker SBF100-32-127 (at any revision) also terminates 

the repetitive inspection requirements of this AD for that aeroplane. 

(6) After 20 August 2011, do not install P/N AE70690E, P/N AE70691E, P/N 

AE99111E or P/N AE99119E brake QD couplings on any aeroplane. 

Ref. Publications: 

Fokker Services SBF100-32-127 dated 20 July 2001, now at Revision 1 dated

06 March 2009 and superseded/replaced by: 

Fokker Services SBF100-32-156 dated 06 March 2009. 

The use of later approved revisions of this document 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. This AD was posted on 19 June 2009 as PAD 09-083 for consultation 

until 17 July 2009. 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. 
EASA AD No.: 2009-0176 

EASA Form 110 Page 3/3 

4. For any question concerning the technical content 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