AD/F100/55 Amdt 1 - Main Landing Gear Main Fitting - 2

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AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/F100/55 and issues the following AD under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

 

Fokker F100 (F28 Mk 100) Series Aeroplanes

 

AD/F100/55

Amdt 1


Main Landing Gear Main Fitting - 2 2/2005

DM

 

 

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: 1. Amend the Aircraft Flight Manual (AFM), Section Limitations, to prohibit the application of brakes during backward movement (push-back) of the aircraft. This may be accomplished by inserting a copy of this Directive into the AFM.

 

2.         Install a placard on the pedestal, next to the parking brake handle, having the following wording:

 

“Application of Brakes During Backward Movement is Prohibited”

 

3.         Inspect the MLG Main Fittings in accordance with the Accomplishment Instructions of Messier-Dowty (SB) F100-32-104, dated 22 August 2002, or later UK CAA approved revision.

 

4.         Whenever a hard or overweight landing is reported and subsequently confirmed by inspection in accordance with the Aircraft Maintenance Manual Chapter 05- 51-01, Table A, inspect the MLG Main Fittings in accordance with the Accomplishment Instructions of Messier-Dowty SB F100-32-104 Revision 2, dated 30 October 2003, or later UK CAA approved revision.

 

5.         After each occasion when braking has been applied during aircraft backward movement in push-back or power-back operation, inspect the MLG Main Fittings in accordance with the Accomplishment Instructions of Messier-Dowty SB F100- 32-104 Revision 2, or later UK CAA approved revision.

 

6.         When cracks are found, determine whether and for how many, flights may be continued before repair or replacement; in accordance with the crack size and location thresholds as listed in Fokker Services SB F100-32-137 Revision 2, dated 9 February 2004, or later CAA-NL approved revision.

 

7.         Irrespective of the results, report all inspection findings to Fokker Services.

 

Note: CAA-NL AD 2002-115/2 refers.

 

Compliance: 1. Before further flight after 4 September 2002.

 

2.         Within 14 days after 4 September 2002.

 

3.         Within 1,000 flight cycles or 6 months after 4 September 2002, whichever occurs first.

 

4.         Before further flight.

 

5.        - Before further flight, if the MLG has not been inspected before in accordance with Messier-Dowty SB F100-32-104, dated 22 August 2002, or later UK CAA approved revision; or,

 

-            Before further flight, if a previous MLG inspection revealed cracks and the aircraft is operating during the so-called “fly-on” period (refer to Requirement 6); or,

 

-          Within the next 50 flight cycles after 22 December 2004, if a previous inspection revealed cracks in the MLG that have subsequently been repaired in accordance with the requirements of Requirement 6; or.

 

-          Within the next 50 flight cycles after 22 December 2004, if a previous inspection revealed no cracks in the MLG.

 

6.         As specified in the Requirement document.

 

7.         Within 7 calendar days after each required inspection.

 

The compliance times for Requirements 1, 2, and 3 remain unchanged by this issue. This Amendment becomes effective on 22 December 2004.

Background: The CAA-NL has received a report concerning a F100 aircraft with Messier-Dowty main landing gear where, upon braking during terminal push-back of the aircraft, the right hand MLG Main Fitting failed. Investigation revealed overload, initiated by a

4.5 mm fatigue crack originating from one of the MLG filler and bleeder ports, which are located on the aft side of the MLG.

 

Amendment 1 is issued in response to a revision of the related CAA-NL AD, which introduces detailed compliance changes while allowing some flexibility in repair times; and adds Mk. 0070 aircraft to applicability.


David Villiers

Delegate of the Civil Aviation Safety Authority 14 December 2004

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 22 December 2004.

Overview

The Airworthiness Directive issued under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1988 (CASR) seeks to address safety issues with Fokker F100 (F28 Mk 100) Series Aeroplanes, specifically those equipped with Messier-Dowty main landing gear units. This directive, issued by the Civil Aviation Safety Authority (CASA) through its delegate David Villiers on 14 December 2004, revises Airworthiness Directive AD/F100/55, aiming to ensure the safe operation of these aircraft by mandating specific actions related to braking during aircraft backward movement and the inspection of main landing gear fittings. The directive was introduced following reports of failures in the main landing gear during terminal push-back, which were traced to fatigue cracks in the main landing gear filler and bleeder ports. The policy objective is to prevent unsafe conditions that could potentially lead to accidents or further damage to the aircraft.

Scope and Application

The Airworthiness Directive issued under the Civil Aviation Act 1988 applies to all Fokker F100 (F28 Mk 100) series aeroplanes, specifically those marked as Mk 0100 and Mk 0070, with all serial numbers, that are equipped with Messier-Dowty main landing gear units. This legislative instrument, which extends to the Commonwealth of Australia, mandates specific actions to address an unsafe condition identified with the main landing gear fittings of these aircraft. The requirement includes amending the Aircraft Flight Manual to prohibit brake application during backward movement of the aircraft, installing a placard to reinforce this prohibition, conducting detailed inspections of the main landing gear fittings under various conditions, and reporting findings to Fokker Services. The compliance deadlines set forth ensure timely action to rectify the identified safety issue. This directive does not specify any exclusions or exemptions but is enforced through subordinate instruments as necessary.

Key Provisions

The Airworthiness Directive AD/F100/55 Amendment 1, issued under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998, sets out specific actions to address an unsafe condition in Fokker F100 (F28 Mk 100) Series Aeroplanes equipped with Messier-Dowty Main Landing Gear (MLG) units. The directive applies to F28 Mk 0100 and Mk 0070 aircraft of all serial numbers (section 2). The requirements include amending the Aircraft Flight Manual (AFM) to prohibit brake application during backward movement (section 1), installing a placard near the parking brake handle indicating that brake application during backward movement is prohibited (section 2), and conducting various inspections of the MLG Main Fittings under different circumstances (sections 3-5). Additionally, it mandates determining flight continuation before repair or replacement when cracks are found (section 6) and reporting all inspection findings to Fokker Services (section 7). The obligations imposed by this directive include updating the AFM, installing the specified placard, and performing inspections as detailed in the requirement section. Operators must ensure that these inspections are conducted before further flights, within specific timeframes, and that all findings are reported to Fokker Services. Compliance timelines vary, with some inspections needing to be completed before further flight and others within certain flight cycles or months from the effective date of the directive (section 7). Breaches of this Airworthiness Directive may result in severe civil or criminal consequences. Non-compliance could lead to grounding of the affected aircraft, fines, and other penalties as stipulated by the Civil Aviation Safety Authority. The maximum penalties for non-compliance are not explicitly stated in the directive but could include substantial fines and potential imprisonment depending on the severity and impact of the breach. It is crucial for operators to adhere to these requirements to ensure the continued airworthiness and safety of the aircraft.

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.