Lufttüchtigkeitsanweisung LTA-Nr.: D-2004

Lufttüchtigkeitsanweisung
LTA-Nr.: D-2004-256R1
ersetzt: D-2004-256
Datum der Bekanntgabe: 18.01.2006
Luftfahrt-Bundesamt
Muster: Fokker
FOKKER F28
AD der ausländischen Behörde:
CAANL AD NL-2005-012 vom 17.10.2005
Geräte-Nr.:
2824
Technische Mitteilungen des Herstellers:
Messier-Dowty Service Bulletin F100-32-110 vom 25.08.2005
Fokker MCNM F100-083 Revision 1 vom 15.04.2004
Betroffenes Luftfahrtgerät:
Fokker
FOKKER F28
- Baureihen:
F28 Mk.0070 (Fokker 70) und Mk.0100 (Fokker 100)
- Werk-Nrn.:
Alle
-- mit installiertem Dowty / Messier-Dowty Hauptfahrwerk der Part-Nummer (P/N)
201072011, P/N 201072012, P/N 201072013, P/N 201072014, P/N 201072015
oder P/N 201072016, das mit dem betroffenen Federbeininnenzylinder der P/N
201072301 oder P/N 201072305 ausgerüstet ist
Betrifft:
FAHRWERK (ATA: 32): Hauptfahrwerk - Federbeininnenzylinder (P/N 201072301 und P/N 201072305)
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten CAA-NL
Airworthiness Directive (AD) und den genannten technischen Mitteilungen des Herstellers zu entnehmen. Alle
erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und
innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
Zustimmung durch das Luftfahrt-Bundesamt.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten CAA-NL Airworthiness Directive (AD) zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten CAA-NL
Airworthiness Directive (AD).
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
CAANL AD NL-2005-012 vom 17.10.2005
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
(LTA-Nr.: D-2004-256 vom 10.06.2004)
Aktenzeichen: (01)T233-502.1/D-2004-256R1
Seite 1 von 1
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Civil Aviation Authority Netherlands
Airworthiness Directive
Caution
This Airworthiness Directive is issued by the Minister of Transport, Public
Works and Water Management in accordance with the Aviation Act 2001
(Wet Luchtvaart), Article 3.22. Airworthiness Directives affect aviation
safety. These are regulations which require immediate attention. No person
Nr.
NL-2005-012
Date :
October 17, 2005
Distribution :
L
Type Certificate Holder :
FOKKER SERVICES B.V.
(formerly Fokker Aircraft B.V.)
F28 Mark 0070 and Mark 0100
may operate an aircraft to which an Airworthiness Directive applies, except
in accordance with the requirements thereof, unless otherwise agreed with
the Authority of the State of Registry (EC2042/2003, M.A.201 & M.A.303).
EASA Type Certificate Nr.
A.037
THIS AIRWORTHINESS DIRECTIVE IS PUBLISHED BY THE CAA-NL :
• acting for and on behalf of the European Aviation Safety Agency (EASA), as Airworthiness Authority (ICAO
Annex 8) of the State of Design for the affected product(s) with reference to 21A.3B (a) and (b); and
• has been approved under EASA reference Number 2005-6363 dated October 14, 2005.
Supersedure : This AD supersedes and cancels BLA 2004-046 dated April 20, 2004.
Subject : LANDING GEAR - MAIN LANDING GEAR SLIDING MEMBER - INSPECTION
Applicability : Fokker Aircraft B.V. Model F.28 Mk.0070 and Mk.0100 aircraft, all serial numbers, if
equipped with Dowty or Messier-Dowty Main Landing Gear Part Number (P/N) 201072011,
201072012, 201072013, 201072014, 201072015 or 201072016, which include sliding member P/N’s
201072301 or 201072305.
Reason : During pushback from the gate of a Fokker 100 (F28 Mark 0100), the sliding member of a
Main Landing Gear (MLG) broke off. The failure occurred during braking while the aircraft was moving
backwards, immediately after the towbar was inadvertently disconnected. The subsequent
investigation of the fractured surface showed that this had been caused by overload, initiated by a
fatigue crack on the aft side of the MLG sliding member, some 3-4 mm above the axle platform. It was
also shown that reverse braking is likely to be the only mode that can cause tensile stresses in this
location, sufficient to result in cracking and subsequent failure. NDT inspections performed on some
operational aircraft and on spare units held by Fokker Services revealed additional MLG units with
cracks in the same area. This condition, if not corrected, could result in further incidents of cracked
MLG sliding members and possible MLG separation. Since an unsafe condition had been identified that
is likely to exist or develop on other aircraft of the same type design, Airworthiness Directives (BLA)
2002-060 and 2004-046 were issued to require, respectively, a one-time inspection and a single
repeat inspection of all (Messier-) Dowty Main Landing Gear units. The results from those inspections
have identified the need for a repetitive inspection on the MLG Sliding Member to establish fleet
safety. For this reason, the present AD requires repetitive magnetic particle inspections of all aircraft
equipped with (Messier-)Dowty Main Landing Gear units and replacement of cracked parts.
Effective date : November 1, 2005
Mandatory Actions and Compliance Times : Required as indicated, unless accomplished previously.
(a)
For aircraft that are not compliant with the requirements of BLA 2002-060 and/or
BLA 2004-046, before the next flight after the effective date of this directive, inspect the MLG sliding
members for cracks in accordance with the Accomplishment Instructions of Messier-Dowty Service
Bulletin (SB) F100-32-110 dated August 25, 2005 or a later CAA(UK) approved revision;
(b)
For all other aircraft, within 2,000 flight cycles after the accomplishment of Messier-Dowty
SB F100-32-103 (Ref. Fokker SBF100-32-133) or Messier-Dowty SB F100-32-105 (Ref. Fokker
SBF100-32-139) or within the next 4 calendar months, whichever occurs later after the effective date
of this directive, inspect the MLG sliding members for cracks in accordance with the Accomplishment
Instructions of Messier-Dowty SB F100-32-110 dated August 25, 2005 or a later CAA(UK) approved
revision;
Note 1: Fokker SBF100-32-144 dated September 19, 2005 also pertains to this subject.
ISSN 0920-1084
Page 2 of 2
AD nr. NL-2005-012
(c)
After compliance with either paragraph (a) or (b) of this directive, at intervals not to exceed 2,000
flight cycles, repeat the inspection of the MLG sliding members in accordance with the Accomplishment
Instructions of Messier-Dowty SB F100-32-110 dated August 25, 2005 or a later CAA(UK) approved revision;
(d)
Each time after a High Drag Load landing, before next flight, magnetically inspect the MLG sliding
members for cracks in accordance with Fokker 70/100 Aircraft Maintenance Manual (AMM), Task 05-51-01220-826-A;
(e)
Each time when the aircraft brakes have been applied during backward movement of the aircraft,
within the next 50 flight cycles thereafter, inspect the MLG sliding members in accordance with Fokker
70/100 AMM, Task 05-51-01-220-876-A;
Note 2: Fokker Manual Change Notification - Maintenance Documentation (MCNM) F100-083 Rev.1 dated
April 15, 2004 contains the procedures related to the requirements of paragraphs (d) and (e) of this directive.
(f)
As of the effective date of this directive, no spare MLG sliding member may be installed on any
aircraft as a replacement part, unless it has been inspected in accordance with the Accomplishment
Instructions of Messier-Dowty SB F100-32-110 dated August 25, 2005 or a later CAA(UK) approved revision;
(g)
When any crack indication is found, before further flight, replace the MLG sliding member with a
serviceable part in accordance with the Fokker 70/100 AMM, Chapter 32-11-08.
(h)
Whatever the results of the inspections as required by this directive, report ALL findings to the Type
Certificate Holder of the aircraft and the Main Landing Gear manufacturer, addresses listed below.
Reference Publication(s) :
Messier-Dowty SB F100-32-103
Messier-Dowty SB F100-32-105
Messier-Dowty SB F100-32-110
Fokker SBF100-32-133
Fokker SBF100-32-139
Fokker SBF100-32-144
Fokker 70/100 AMM
Fokker MCNM F100-083 R1
Remarks :
- Operators of the affected aircraft may obtain copies of the referenced service information upon request directly from
Messier-Dowty Ltd., Customer Support, Cheltenham Road, Gloucester GL2 9QH, United Kingdom;
telephone (44) 1452-712-424; facsimile (44) 1452-713-821; website www.messier-dowty.com; or from
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 [email protected].
- Compliance with this directive must be recorded in the proper Aircraft Log Book(s).
- Where applicable, the requirements of this directive must be integrated into the aircraft’s Maintenance Schedule.
Address inquiries concerning this AD to :
Civil Aviation Authority of The Netherlands, Airworthiness Inspectorate, Section Product Certification, P.O. Box 575, 2130 AN
Hoofddorp, The Netherlands; telephone +31-23-566-3155; facsimile +31-23-566-3006; e-mail [email protected].