AD/F100/72 - Landing Gear - Brake Control Levers

The AD applies directly to owners and operators of Fokker Aircraft B.V. Model F28 Mark 0070 and Mark 0100 aeroplanes whose airframes have serial numbers in the range 11244 through 11585 (Applicability). That list defines the population of aircraft to which the mandatory measures apply. Because airworthiness directives bind the operator/maintenance organisation responsible for continuing airworthiness, the practical burden falls on the registered operator(s), their contracted maintenance organisations, and ultimately the owners who finance maintenance and parts procurement.

Decision‑makers within affected organisations include maintenance control, the licensed engineers who must carry out measurements and replacements in accordance with the referenced Service Bulletin (Section 3 of Fokker SB F100‑32‑142), and the accountable manager who decides where inspections are scheduled in relation to operational commitments. The AD does not name specific individuals beyond the issuing delegate of the Civil Aviation Safety Authority, but the instrument’s structure requires an operator to determine applicability against their fleet records and to schedule inspections within the compliance timeframe.

Other stakeholders affected indirectly include suppliers of replacement brake control levers, because the AD will create demand for serviceable parts where levers require replacement; and aviation regulators outside Australia with overlapping jurisdiction or shared certification interests, since the AD cites CAA‑NL and EASA references (Background). The AD explicitly references actions to be taken “in accordance with Section 3” of a Fokker Service Bulletin or a later CAA‑NL approved revision, which brings the manufacturer (Fokker Services) and the approving national authority (CAA‑NL) into the compliance chain. Finally, because the AD addresses a failure mode that can cause uncommanded braking and possible loss of control during ground phases, it affects flight operations risk assessments and may require operational adaptations (e.g. scheduling additional maintenance or grounding aircraft until compliance).

The AD does not extend to other Fokker types or serial numbers outside the cited range, nor does the text broaden applicability beyond those identifiers. No exemptions, alternative methods of compliance, or deferred action regimes are stated in the AD text itself; compliance must follow the SB or a later CAA‑NL approved revision.

Duties imposed by the AD are specific and measurable. The operator/maintenance organisation must:

• Determine applicability by checking whether an aircraft’s serial number falls within 11244 through 11585 (Applicability).
• Inspect the brake control levers for excessive wear in accordance with Section 3, Accomplishment Instructions, of Fokker Service Bulletin F100‑32‑142 dated 12 August 2005, or a later CAA‑NL approved revision (Requirement).
• Measure remaining material thickness at the attachment holes and act on the measurement: where remaining thickness is less than 2 mm, replace the affected brake control levers with serviceable parts in accordance with Section 3 of the SB or later approved revision; where remaining thickness is between 2 mm and 4 mm, replace the affected brake control levers in accordance with Section 3 of the SB or later approved revision (Requirement).
• If no significant wear is found, no further action is required and the aircraft may be returned to service (Requirement).
• Complete inspections within the stated compliance window: within the next 1,500 flight cycles or 12 months after the effective date of the AD, whichever occurs first. The AD further requires some actions to be performed before further flight or in accordance with the schedule in paragraph B(9) of Section 3 of the SB (Compliance).

Rights, as expressed (or implied) in the AD, are limited and procedural. The AD permits use of a later CAA‑NL approved revision of the Fokker Service Bulletin rather than the exact 12 August 2005 version. That creates a right for an operator to follow an updated SB if that revision has CAA‑NL approval, which can be important where Fokker or the authority issue refinements. The AD also makes explicit that where inspections show “no significant wear” the aircraft may be returned to service; that is an immediate operational right contingent on the inspection result.

The AD does not set out a formal process for requesting alternative means of compliance (AMOC) or relief within the text. It does not specify records retention requirements, but in aviation practice an AD implies that compliance must be recorded in the maintenance log; however that implication is not detailed in the instrument provided. The AD also does not specify who must fund parts or maintenance; responsibility for funding follows from the duty to ensure the aircraft is airworthy, which falls to the operator/owner as the practical burden. The AD does not grant a right to defer compliance beyond the specified window; it does allow for urgent actions “before further flight” in cases where immediate action is necessary.

The AD text itself does not include express penalty provisions or a sanctions schedule. It states the safety directive, prescribes inspection and replacement actions, identifies the compliance timeframe, and records the issuing authority and effective date, but it does not set out criminal or civil penalties, nor specific enforcement mechanisms, within the document text provided. The only enforcement indicator present is administrative: the instrument is issued by the Civil Aviation Safety Authority (Delegate James Coyne), which is the regulator authorised to issue such directives (signature block and identifying information).

In aviation regulatory regimes, compliance with ADs is a prerequisite to maintaining airworthiness and lawful operation; non‑compliance commonly renders an aircraft unairworthy and exposes the operator to regulatory enforcement action. That general regulatory context is not stated explicitly in the AD text supplied; the AD does not, for example, recite statutory penalty sections, specify suspension or revocation procedures, or provide a fine table. The AD does, however, include procedural enforcement cues: it prescribes that an aircraft may be returned to service only where “no significant wear is found” or after required replacement actions have been completed in accordance with the SB (Requirement). This prescriptive return‑to‑service linkage creates an operational enforcement point because maintenance certification of return to service would need to reference compliance with the AD.

The AD references other authorities (CAA‑NL AD NL‑2005‑011 and EASA Reference No 2005‑2602 dated 29 August 2005), which indicates regulatory coordination; those documents may carry their own enforcement or penalty frameworks in their jurisdictions, but those are outside the text provided. Where an AD is effective, aviation authorities typically monitor compliance through continuing airworthiness processes and audit inspections; however, the present text does not state specific monitoring, audit, or penalty procedures.

Where an operator fails to comply, the practical consequences are that the aircraft would be operating in a condition identified in the Background as capable of producing unintended braking and potential loss of control. That safety consequence itself informs likely regulatory enforcement, but is not a penalty specified in the AD. Users of this directive should therefore treat enforcement and penalties as governed by the broader aviation safety regulatory framework and the relevant national authority’s enforcement policies, rather than by provisions contained in this single AD.

The AD explicitly cross‑references other regulatory instruments and manufacturer documentation, which creates interaction points rather than standalone law. It requires compliance with Fokker Service Bulletin F100‑32‑142 Section 3 or a later revision approved by the CAA‑NL, tying the AD to a manufacturer’s technical instructions and the approving authority’s oversight (Requirement). It also notes CAA‑NL AD NL‑2005‑011 and EASA Reference No 2005‑2602 dated 29 August 2005 (Requirement; Background), signalling harmonisation or parallel action among aviation authorities. That cross‑reference means operators may need to consult both the SB and the corresponding foreign ADs or EASA reference to understand the full compliance context.

The AD sits within the broader framework of airworthiness regulation where national authorities issue directives to mandate corrective action for identified unsafe conditions. Although the AD text supplied does not reproduce statutory enabling provisions, standard practice is that ADs derive their force from the national aviation safety regulator’s statutory powers. The AD’s linkage to CAA‑NL and EASA documents suggests coordination where certification or continuing airworthiness responsibilities are shared across jurisdictions for this aircraft type. An operator subject to multiple jurisdictions would need to map this AD against the obligations imposed by the state of registry and any other applicable authorities.

The requirement to follow a “CAA‑NL approved revision” of the Service Bulletin introduces a compliance interaction: the operator must be aware of subsequent SB revisions and CAA‑NL approvals. If an operator were in a jurisdiction that requires different approval or uses an alternative method of compliance, they would need to reconcile the AD’s specified approval route with local regulatory processes. The AD does not expressly address conflicts between this AD and other national ADs; rather, by citing CAA‑NL and EASA references, it implicitly acknowledges parallel regulatory action and directs operators to the manufacturer SB as the technical standard.

Because the AD is focused on maintenance actions (inspection and part replacement), it interacts practically with maintenance regulation, continuing airworthiness management requirements, and operational conformity to airworthiness certificates. The AD’s effective date and compliance windows determine scheduling and may interact with operational authorisations such as air operator certificates, maintenance organisation approvals, and continuing airworthiness declarations; those operational legal instruments are not quoted in the AD text but will be the mechanisms through which compliance is recorded and enforced.

The AD identifies itself as AD/F100/72 and carries the designation 11/2005. The signature block shows it was issued by James Coyne, Delegate of the Civil Aviation Safety Authority, on 16 September 2005, and the AD states “This Airworthiness Directive becomes effective on 27 October 2005.” The Requirement references Fokker Service Bulletin F100‑32‑142 dated 12 August 2005 and allows the use of “a later CAA‑NL approved revision,” thereby providing a mechanism for technical amendment of the required procedures via SB revisions approved by the Netherlands’ authority (Requirement). The AD also cites external ADs and references , CAA‑NL AD NL‑2005‑011 and EASA Reference No 2005‑2602 dated 29 August 2005 , which indicates contemporaneous regulatory instruments of record.

Beyond these items, the supplied text does not disclose any subsequent amendments to AD/F100/72 itself, nor does it list prior versions or a history of textual changes to the AD. There is no amendment log, no revocation clause, and no statement that the AD supersedes or is superseded by other ADs within the document. The presence of multiple repeated headings and the inclusion of the Service Bulletin revision mechanism suggests the drafters intended the SB approval process to be the locus of technical updates rather than repeated formal amendment of the AD text.

If a later CAA‑NL approved revision of the SB exists, the AD explicitly permits reliance on it. Therefore the practical amendment pathway is: Fokker revises the Service Bulletin, CAA‑NL approves that revision, and operators may then use the later approved revision to meet the AD’s requirements. The AD itself does not list a timeline or criteria for acceptance of SB revisions; it simply references CAA‑NL approval as the condition for accepting later revisions. No retroactive amendments or transitional provisions are contained in the provided text.

For record‑keeping and legal certainty, affected operators should archive the AD file copy that includes the effective date (27 October 2005), the SB version used for compliance, and any CAA‑NL approval documents for later SB revisions used. The AD’s allowance for later approved revisions creates an operational amendment path but does not change the AD’s stated effective date or the initial compliance windows unless a formal superseding AD is issued, which is not recorded in the text provided.

The AD text supplied contains no litigation history. It does not reference any legal challenges, court decisions, or administrative appeals arising from this directive. The document is an administrative instrument; it records the issuer (Delegate of CASA), the dates (16 September 2005 signing, 27 October 2005 effective), the referenced service bulletin (F100‑32‑142 dated 12 August 2005), and related foreign ADs (CAA‑NL AD NL‑2005‑011 and EASA Reference No 2005‑2602 dated 29 August 2005), but it contains no account of disputes, compliance prosecutions, or adjudications.

Because the AD identifies a safety issue that could cause loss of control during ground handling, it establishes factual predicates that could be relevant in later liability or enforcement proceedings; however, the AD itself does not report any legal proceedings arising from the incident described in the Background. The aircraft event that prompted the AD (extreme pedal angle difference, higher LH brake temperatures, worn attachment holes) is described as the factual basis for the AD rather than as part of litigation.

In the absence of recorded litigation in the text, a researcher or practitioner seeking litigation history must consult external records: regulatory enforcement actions by CASA (or its successors), national aviation tribunal records, civil litigation involving operators or manufacturers, or communications between the manufacturer and aviation authorities. Those records are not included in the AD text and therefore cannot be reported here.

Several practical traps for operators and maintenance organisations arise directly from the AD text:

• Narrow applicability window. The AD applies only to aircraft with serial numbers 11244 through 11585 (Applicability). Operators must verify airframe serial numbers carefully; overlooking aircraft on lease or with changed registration could lead to non‑compliance. The AD does not provide guidance on leased aircraft or on responsibilities where control and registration differ, so responsibility rests on the operator to identify affected units.

• Dependence on the Service Bulletin. The AD requires inspection “in accordance with Section 3. Accomplishment Instructions of Fokker Service Bulletin F100‑32‑142 dated 12 August 2005 or a later CAA‑NL approved revision” (Requirement). The AD does not reproduce the measurement technique, inspection intervals beyond the compliance window, or the content of paragraph B(9) of Section 3. Operators must obtain the SB and any later approved revisions. Failure to follow the precise SB procedure, or reliance on an unapproved SB revision, risks non‑compliance.

• Ambiguous phrasing that leads to a single practical threshold. The AD sets two replacement conditions: less than 2 mm, and between 2 mm and 4 mm (Requirement). Both bands require replacement, which functionally means any remaining thickness under 4 mm triggers replacement. Operators should not treat the 2 mm and 2-4 mm distinctions as permitting different maintenance actions; both require replacement. The AD also permits return to service when “no significant wear” is found; the SB will determine what “no significant wear” means and how to reconcile it with the thickness thresholds.

• Compliance timing nuances. The compliance statement includes multiple timing instructions: a general window of within 1,500 flight cycles or 12 months from effective date, whichever first; an instruction “before further flight” in a subparagraph; and a schedule reference to paragraph B(9) of Section 3 of the SB. Operators must read the SB’s paragraph B(9) to determine whether certain actions have a more urgent deadline than the global 1,500 cycles/12 months window. Failure to sequence inspections and replacements correctly could leave an aircraft grounded or operating in breach of the AD.

• Parts availability and traceability. The AD requires replacement with “serviceable parts in accordance with Section 3” (Requirement). The AD does not define what constitutes a serviceable part or whether certified new parts are mandatory; the SB will have the technical and approval criteria. Operators must ensure parts are correctly certified, compatible with the serial number range, and documented as installed to show AD compliance.

• Jurisdictional interaction. The AD references CAA‑NL and EASA documents (Requirement; Background). If an operator is registered in a jurisdiction that uses different approval processes for SB revisions or AMOCs, they must reconcile those processes with the AD’s reference to CAA‑NL approval. The AD does not provide a path for alternate compliance approvals in jurisdictions other than via the SB/C AA‑NL approved revision route.

• No penalties or enforcement language. The AD contains no explicit penalty clauses in the text provided. That does not mean enforcement is absent, but operators should not assume the AD is advisory. The lack of explicit penalty text is a drafting omission for those seeking statutory enforcement detail; operators should consult their regulator for enforcement policy.

• Operational consequences of inspection outcomes. If inspection reveals wear below thresholds and replacement is required, the operator must plan for aircraft downtime, parts procurement, and maintenance certification. The AD’s return to service is conditional; until replacement is complete the aircraft may not be economically usable.

• Interpreting the Background. The Background explains the safety rationale , worn holes on RH MLG levers, and an unrelated normal brake control valve failure. The operator should not conflate the unrelated valve failure with the lever wear when documenting compliance; the AD requires lever inspection irrespective of other component histories.

In short, the AD’s reliance on a separate Service Bulletin for technical detail, the multiple timing references, and the requirement to use a later CAA‑NL approved revision if available create multiple operational dependencies. The maintenance organisation must obtain and follow the SB, manage parts and downtime, and document compliance relative to the effective date (27 October 2005).

Compliance is a procedural sequence anchored to the AD’s applicability, the referenced Service Bulletin, and the AD’s time limits. The following steps, grounded in the AD text, describe what an operator should do:

1. Confirm applicability. Check the aeroplane serial number against the AD’s applicability range (11244 through 11585). If an airframe is within that range, the AD applies (Applicability).

2. Acquire the referenced documentation. Obtain Fokker Service Bulletin F100‑32‑142 dated 12 August 2005 and verify whether any later CAA‑NL approved revision exists. The AD permits using a later CAA‑NL approved revision in lieu of the dated SB (Requirement). Also, record the CAA‑NL AD NL‑2005‑011 and EASA Reference No 2005‑2602 references for cross‑traceability (Background).

3. Schedule inspection within the compliance window. Plan to carry out the required inspection of the brake control levers within 1,500 flight cycles or 12 months from the AD’s effective date, 27 October 2005, whichever occurs first (Compliance). Note that some actions may be required “before further flight” or according to paragraph B(9) of Section 3 of the SB; consult the SB to decide sequencing and urgency (Compliance).

4. Perform inspection per SB Section 3. Use the procedures and measurement methods specified in Section 3, Accomplishment Instructions, of the SB to inspect for excessive wear (Requirement). The SB contains the technical instructions for measuring remaining material thickness and likely provides tolerances, measurement positions, and any necessary removal or disassembly steps. Do not substitute an alternative inspection method unless a later CAA‑NL approved revision authorises it.

5. Measure remaining material thickness and act on results. If the remaining material thickness at the attachment holes is less than 2 mm, replace the affected brake control levers with serviceable parts in accordance with Section 3 of the SB or later CAA‑NL approved revision. If remaining thickness is between 2 mm and 4 mm, likewise replace the affected levers per Section 3 of the SB (Requirement). If the inspection finds “no significant wear” as defined by the SB, no further action is required and the aircraft may be returned to service (Requirement).

6. Install replacement parts per SB. Where replacement is required, fit serviceable brake control levers as specified by Section 3 of the SB or a later CAA‑NL approved revision, ensuring parts compliance and traceability to the SB’s instructions (Requirement).

7. Record compliance in maintenance records. Although the AD text does not specify recordkeeping requirements, standard airworthiness practice requires maintenance actions and compliance with ADs to be recorded in the aircraft’s maintenance log and continuing airworthiness records. Record the SB revision used, measurements taken, parts installed (part numbers and serials if applicable), and the certificate of release to service signed by an appropriately authorised engineer.

8. Return to service only when compliant. The AD permits return to service where “no significant wear” is found or after required replacements have been completed in accordance with the SB (Requirement). Do not operate the aircraft commercially or release it to service if the necessary inspections/replacements have not been performed consistent with the AD.

9. Monitor for SB revisions and regulator approvals. Since the AD allows use of later CAA‑NL approved SB revisions, monitor CAA‑NL and manufacturer communications for updated SBs that may alter inspection technique, thresholds, or scheduling. If an updated CAA‑NL approved SB is issued, operators may use it to meet the AD.

10. Coordinate with regulator where uncertainty exists. If doubt exists about compliance timelines, alternative methods, or if an aircraft has been modified in a way that affects the brake control levers, consult the Civil Aviation Safety Authority or the competent authority for guidance. The AD itself does not provide an AMOC procedure, so regulatory consultation is prudential when alternative remedies are considered.

Financially, the AD imposes costs on operators in the form of inspection labour, potential parts replacement and associated downtime. The AD does not quantify costs or specify funding responsibility; practical compliance therefore requires the operator or owner to budget for inspection and possible replacement and to source serviceable parts that meet the SB’s requirements.

Following these steps, with meticulous records linking actions to the AD’s effective date (27 October 2005) and the Service Bulletin version used, will satisfy the procedural requirements as stated in the AD text.