Commonwealth legislation

AD/F100/64 - Main Landing Gear Main Fitting - 3

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legislative instrument

Plain English Summary

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This directive requires operators of Fokker F100 aeroplanes fitted with Messier‑Dowty main landing gear to inspect both main landing gear main fittings, repair or replace any defective parts per the manufacturer service bulletins, and report findings to Fokker Services within seven days. It sets mandatory time limits for compliance (based on flight cycles or a three‑month deadline) after a reported in‑service failure and allows limited continuation of flight only where crack‑size thresholds permit.

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Current sections

Direct links to the current provisions in AD/F100/64 - Main Landing Gear Main Fitting - 3.

Fokker F100 (F28 Mk 100) Series Aeroplan

Fokker F100 (F28 Mk 100) Series Aeroplanes

AD/F100/64	Main Landing Gear Main Fitting - 3	6/2005

Applicability:	Model F.28 Mk 0100 and Mk 0070 aircraft, all serial numbers, if equipped with Messier-Dowty (formerly Dowty Aerospace Gloucester) MLG units.
Requirement:	Inspect and, as necessary, repair both MLG Main Fittings in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin (SB) F100-32-106 dated 18 February 2005, or later UK CAA approved revision.Whenever cracks are found, determine whether (and for how many) flights may be continued, prior to repair or replacement, in accordance with the crack size and location thresholds as specified in Fokker Services SB F100-32-141 dated 18 February 2005, or later CAA-NL approved revision.Irrespective of the inspection results, within 7 days after accomplishment of the inspection, report all findings to Fokker Services.Note: CAA-NL AD NL-2005-002 refers.
Compliance:	Within 2,000 flight cycles since the last inspection in accordance with Messier-Dowty SB F100-32-104 Revision 2, and Fokker Services SB F100-32-137 (as required by AD/F100/55 Amdt 1; CAA-NL AD 2002-115/2 refers), or within 3 months after 9 June 2005, whichever occurs later.
	This Airworthiness Directive becomes effective on 9 June 2005.
Background:	Recently, an empty Fokker 100, which was being moved for maintenance, suffered a failure of the left hand MLG Main Fitting. The MLG Main Fitting broke into two pieces, whereby the lower part including the Sliding Member, Wheels and Brakes separated from the upper Main Fitting part. Preliminary findings indicate failure due to a fatigue crack in the Main Fitting. AD/F100/55 Amdt 1 (CAA-NL AD2002-115/2) still applies, and although this Directive requires a second one-time inspection for cracks, the CAA-NL still consider this to be an interim action.

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David Villiers
Delegate of the Civil Aviation Safety Authority

29 April 2005

AD/F100/64

Main Landing Gear Main Fitting - 3

6/2005

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

Fokker F100 (F28 Mk 100) Series Aeroplan Fokker F100 (F28 Mk 100) Series Aeroplanes

Fokker F100 (F28 Mk 100) Series Aeroplanes

AD/F100/64	Main Landing Gear Main Fitting - 3	6/2005

Applicability:	Model F.28 Mk 0100 and Mk 0070 aircraft, all serial numbers, if equipped with Messier-Dowty (formerly Dowty Aerospace Gloucester) MLG units.
Requirement:	Inspect and, as necessary, repair both MLG Main Fittings in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin (SB) F100-32-106 dated 18 February 2005, or later UK CAA approved revision.Whenever cracks are found, determine whether (and for how many) flights may be continued, prior to repair or replacement, in accordance with the crack size and location thresholds as specified in Fokker Services SB F100-32-141 dated 18 February 2005, or later CAA-NL approved revision.Irrespective of the inspection results, within 7 days after accomplishment of the inspection, report all findings to Fokker Services.Note: CAA-NL AD NL-2005-002 refers.
Compliance:	Within 2,000 flight cycles since the last inspection in accordance with Messier-Dowty SB F100-32-104 Revision 2, and Fokker Services SB F100-32-137 (as required by AD/F100/55 Amdt 1; CAA-NL AD 2002-115/2 refers), or within 3 months after 9 June 2005, whichever occurs later.
	This Airworthiness Directive becomes effective on 9 June 2005.
Background:	Recently, an empty Fokker 100, which was being moved for maintenance, suffered a failure of the left hand MLG Main Fitting. The MLG Main Fitting broke into two pieces, whereby the lower part including the Sliding Member, Wheels and Brakes separated from the upper Main Fitting part. Preliminary findings indicate failure due to a fatigue crack in the Main Fitting. AD/F100/55 Amdt 1 (CAA-NL AD2002-115/2) still applies, and although this Directive requires a second one-time inspection for cracks, the CAA-NL still consider this to be an interim action.

AD/F100/64 - Main Landing Gear Main Fitting - 3

Plain English Summary

Deep dive

Current sections

Fokker F100 (F28 Mk 100) Series Aeroplanes

Fokker F100 (F28 Mk 100) Series Aeroplanes

AD/F100/64

AD/F100/64

Main Landing Gear Main Fitting - 3

Main Landing Gear Main Fitting - 3

6/2005

6/2005

Source text

Fokker F100 (F28 Mk 100) Series Aeroplan Fokker F100 (F28 Mk 100) Series Aeroplanes

Fokker F100 (F28 Mk 100) Series Aeroplanes

AD/F100/64 AD/F100/64

AD/F100/64

Main Landing Gear Main Fitting - 3 Main Landing Gear Main Fitting - 3

Main Landing Gear Main Fitting - 3

6/2005 6/2005

6/2005