AD/BELL 212/4 Amdt 22 - Airworthiness Limitations

The AD builds on several interlocking technical and regulatory concepts that determine the required actions and their scope.

Airworthiness Directive as regulatory instrument. The AD is imposed under subregulation 39.1(1) of CAR 1998 and framed as the action "that the delegate considers necessary to correct the unsafe condition" (opening paragraph). The AD therefore functions as a prescriptive regulatory instrument that converts an identified safety hazard into mandatory maintenance and operational actions for the affected aircraft and parts.

Mandatory Airworthiness Limitations Schedule. Requirement 1 ties retirement obligations to the Mandatory Airworthiness Limitations Schedule, Section 4, of the Bell 212 Maintenance Manual (Revision 5 or later). That schedule is treated as an incorporated technical standard for retirement lives, subject to the AD’s listed exceptions and additions (Requirement 1). In practical terms, this means operators must follow the manual's Section 4 retirement lives unless the AD modifies or augments them.

Retirement Index Number (RIN). Requirement 2 introduces the Retirement Index Number concept as the metric for accumulated life on main rotor mast and trunnion components. The AD requires operators of aircraft fitted with specified mast or trunnion part numbers to "determine the accumulated Retirement Index Number (RIN), inspect and action in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52." The RIN is therefore the core life-counting measure for these components in Australian compliance with the AD.

Part-specific prohibitions and retirement lives. The AD contains a concise table inserting explicit retirement lives for selected parts and a categorical prohibition: certain float landing gear crosstube assemblies are labelled "Not eligible for service on Australian helicopters" (table under Requirement 1). These entries are discrete deviations or additions to the maintenance manual schedule and operate immediately upon the AD’s effectiveness.

Reference to external technical requirements. Requirement 2 imports the FAA Emergency AD 2000-15-52 by reference for technical inspection criteria and remedial actions. The AD provides where to obtain the FAA AD (FAA Internet site or the Authority). That creates a cross-jurisdictional compliance dependency: Australian operators must implement FAA-prescribed inspection procedures and actions.

Safety rationale: metal fatigue and geometry tolerance. The Background explains the causal mechanism prompting Amendment 22. A cracked main rotor mast was metallurgically attributed to fatigue concentrated at snap ring groove radii smaller than the 0.020 inch minimum allowable dimension. The FAA’s review identified two consequential needs: insertion of corrected RIN counting procedures and more stringent controls for fatigue on mast and trunnion components. The AD therefore couples life-limits and inspection requirements to a specific metallurgical failure mode and a dimensional non-conformance.

Temporal and administrative structure. The AD revokes Amendment 21 and supersedes it; it restates Requirement 1 (reformatted) and maintains Requirement 2 additions. The Compliance section prescribes when actions must be completed, and the AD is signed by a CASA delegate, effective 9 August 2000, and notified in the Gazette on that date.

Together, these concepts convert a technical failure mode into a set of enforceable maintenance tasks and part-status rules, linked to a specific maintenance manual revision and to an FAA emergency directive for technical procedure.

The AD directly and indirectly imposes obligations and consequences on a defined set of actors, identifiable from the Applicability, Requirement and Compliance paragraphs.

Operators and owners of Bell 212 helicopters. Requirement 1 applies to "All Model 212 helicopters." That means every owner/operator of a Model 212 airframe registered in Australia, or operating under Australian regulatory jurisdiction, is within the AD’s scope for the component retirement obligations that reference the Bell 212 Maintenance Manual, Section 4 (Requirement 1). These parties are the primary payers of the compliance costs , they must retire parts at specified intervals and replace or repair components accordingly.

Operators and owners with specific mast or trunnion part numbers installed. Requirement 2 applies only to Model 212 helicopters fitted with main rotor mast part numbers 204-011-450-001, -007, -105, -113, or -119, or main rotor trunnion part number 204-011-105-001, or -103. Owners/operators of aircraft fitted with these part numbers must determine accumulated RIN and perform inspections per FAA Emergency AD 2000-15-52. That subset faces immediate inspection and potential grounding or component removal if RIN or inspection findings require it.

Maintenance organisations and licensed engineers. Compliance requires reference to the Bell 212 Maintenance Manual, calculation or verification of RIN, and performance of the inspections specified in the FAA AD. Licensed maintenance organisations and engineers carrying out these tasks are implicated operationally. They are responsible for applying the retirement schedule, interpreting the manual and the FAA AD technical instructions, and carrying out any removals, inspections or repairs.

Parts suppliers and inventory managers. The AD inserts specific retirement lives for part numbers and declares specified float landing gear crosstube assemblies "Not eligible for service on Australian helicopters." Suppliers and operators holding stock of those part numbers must either remove them from Australian service inventories or otherwise ensure they are not installed on Australian-registered Model 212 helicopters. That affects procurement, spares inventories and resale options for those part numbers.

Regulator and CASA delegate. The AD is issued by a CASA delegate under subregulation 39.1(1) and is signed by David Alan Villiers (8 August 2000). The delegate is the decision-maker who revoked Amendment 21 and issued Amendment 22. The Authority is also an access point for the referenced FAA AD (Note under Requirement 2). CASA and its delegates therefore hold the enforcement and interpretive role vis-a-vis this AD.

Foreign authorities and manufacturers. The AD explicitly imports technical instruction from the FAA Emergency AD 2000-15-52 and references Bell Helicopter Textron’s maintenance manual (Revision 5 or later). Bell and the FAA are therefore stakeholders for the technical content (as noted in Background: "Requirement 2, developed by Bell and the FAA"). While the AD is an Australian instrument, its technical foundation intersects with US regulatory and manufacturer material.

Indirectly affected parties. Downtime, replacement parts costs and potential grounding will affect charter clients, employers that rely on the aircraft, insurers, and any third parties that contract flight services. While not named in the AD, these parties will experience the economic and operational consequences that flow from compliance actions undertaken by operators.

In sum, the AD most directly binds Australian operators/owners of Bell 212 helicopters, particularly those with specified mast or trunnion part numbers, and secondarily affects maintenance organisations, parts suppliers and the regulator. The AD assigns mandatory technical obligations that these actors must execute or manage.

This section lists the concrete duties imposed by the AD and the limited operational rights or options that the AD expressly provides.

Primary duties

• Retire components at prescribed times. Requirement 1 requires operators to "Retire components from service at the times specified in the Mandatory Airworthiness Limitations Schedule, Section 4, of the Bell 212 Maintenance Manual (Revision 5 or later)," subject to the AD’s listed exceptions and additions. The AD therefore replaces or supplements the manual’s retirement list for the parts identified in the table under Requirement 1.

• Comply with part-specific retirement lives and prohibitions. The AD’s table prescribes explicit retirement lives for particular part numbers (for example: skid landing gear aft cross tube 205-050-400-035, retirement life 500 hours; skid landing gear aft cross tube 205-050-400-053, retirement life 1000 hours; drive link to rotating swashplate bolts 20-057-5-30D, retirement life 500 hours). The table also lists multiple float landing gear crosstube assembly part numbers and labels them "Not eligible for service on Australian helicopters." Operators must therefore ensure these part numbers are not used in Australian service and that the specified parts are retired according to the indicated hours where a retirement life is provided.

• Determine RIN and inspect certain components. Requirement 2 requires operators of helicopters fitted with the listed mast or trunnion part numbers to determine the accumulated Retirement Index Number (RIN), and to perform inspections and any required actions "in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52." The AD therefore obliges operators to obtain and follow the FAA AD’s technical inspection and action criteria for those parts.

Timing duties

• For Requirement 1: comply "at the times specified in the Requirement document." That points to the Manual Section 4 schedule and the AD’s table.

• For Requirement 2: for paragraph (a) of the Requirement document, action must be taken "before further flight after 9 August 2000," unless already accomplished. For other required actions in the FAA AD, comply "as specified in the Requirement document."

Procedural duties

• Use of a specified manual revision. Requirement 1 requires retirement times per Bell 212 Maintenance Manual Section 4, Revision 5 or later. That confines compliance to a specified manual baseline, which channels operators to a particular edition for life-limit values.

• Follow FAA technical requirements. For RIN inspection and actions, operators must follow the FAA emergency AD technical material. The AD gives two means of obtaining that document: the FAA Internet site or from the Authority (Note under Requirement 2).

Rights and options expressly provided

• Access to technical material. The AD explicitly authorises obtaining the FAA AD from the FAA site or from CASA, providing operators with the route to the technical instructions they must follow.

• Applicability carve-out. Requirement 2 applies only to helicopters with specified mast/trunnion part numbers. Operators whose helicopters do not carry those part numbers do not have the RIN/inspection duty under Requirement 2.

• No substitution of methods in the AD text. The AD does not provide alternative compliance options or equivalent means of compliance inside the document itself. The only allowed reference is to the Maintenance Manual (Revision 5 or later) and to FAA Emergency AD 2000-15-52 for technical requirements. Any departure from those prescribed paths is not stated in the AD.

Duties not specified in the document

• The AD does not specify reporting obligations, record-keeping specifics, or explicit consequences for non-compliance within its text. It is issued under CAR 1998 subregulation 39.1(1), which is the empowering provision. The AD thus imposes mandatory technical duties but leaves enforcement mechanics and ancillary procedural obligations to the broader regulatory framework and established practice.

In summary, the AD creates discrete, binding maintenance duties tied to a manual and to an FAA emergency AD, prescribes specific retire-by times and part exclusions, sets an urgent inspection deadline for certain mast/trunnion part numbers, and channels operators to specified materials for technical compliance.

The AD itself sets mandatory technical requirements and is issued by a CASA delegate under subregulation 39.1(1) of CAR 1998 (opening paragraph). It is notified in the Commonwealth Gazette on 9 August 2000 (final line). The instrument therefore operates as an administrative direction with legal force founded on CAR 1998.

Legal basis and issuing authority

• The AD is expressly issued under subregulation 39.1(1) of CAR 1998. The text frames the AD as "the action that the delegate considers necessary to correct the unsafe condition" and sets the circumstances and methods for compliance (opening paragraph). The AD is signed by a CASA delegate, David Alan Villiers, on 8 August 2000, and becomes effective 9 August 2000.

Specified enforcement mechanisms

• The AD text prescribes compliance obligations and effective dates, but it does not include an express provision enumerating sanctions or penalties for non-compliance within this document. The AD’s compliance paragraph specifies when actions must be completed (for example, Requirement 2 actions required "before further flight after 9 August 2000" for paragraph (a)), indicating that continuing operation without completing required actions would be inconsistent with the AD.

Relationship to broader enforcement framework

• Because the AD is issued under CAR 1998, enforcement of non-compliance would be located within the general regulatory and enforcement regime established by those regulations (the AD does not repeat those enforcement provisions). The AD should therefore be read as a mandatory regulatory instrument whose compliance is expected under the CAR framework. This AD is notified in the Gazette, which provides public legal notice of its existence and effective date.

Practical enforcement implications derivable from the instrument

• Immediate compliance requirement for certain inspections. Requirement 2 contains an urgent compliance timing: some inspections or actions must be done "before further flight after 9 August 2000" for paragraph (a) of the Requirement document, unless already accomplished. The practical effect is that an aircraft with the specified mast or trunnion part numbers must not be flown further until the RIN is determined and the required inspection/action performed where paragraph (a) applies.

• Prohibition on specific parts. The table in Requirement 1 designates certain float landing gear crosstube assembly part numbers as "Not eligible for service on Australian helicopters." That has the legal effect of forbidding their installation in Australian-registered operations, and it therefore constrains allowed parts during maintenance and reconditioning.

Limitations in the AD text

• The AD does not state the investigatory, corrective action or enforcement steps CASA will take in case of non-compliance, nor does it quantify fines, suspensions, or other penalties. Those are matters that would be controlled by the broader regulatory enforcement procedures under CAR 1998 and agency policy and practice, none of which are reproduced or referenced in detail in this AD.

Information channels and documentation

• The AD provides a mechanism for obtaining the technical requirements for Requirement 2 by directing operators to FAA AD 2000-15-52 (available from the FAA website or from CASA). This is a compliance facilitation step rather than an enforcement provision, but it is integral to implementation because the FAA AD contains the technical inspection and action criteria which operators must follow.

In short, AD/BELL 212/4 Amdt 22 is a mandatory CASA instrument grounded in CAR 1998, it prescribes immediate technical requirements with specified timings and part prohibitions, and it relies on the wider regulatory enforcement machinery for compliance assurance and penalties, none of which are detailed inside the AD itself.

The AD operates as part of the airworthiness regulatory web that intersects technical manuals, foreign directives and the Civil Aviation Regulations. The document itself identifies specific points of interaction.

Primary statutory foundation

• CAR 1998, Part 39. The AD is issued under subregulation 39.1(1) of CAR 1998 (opening paragraph). That situates the AD within the statutory airworthiness directive regime. The AD’s operative force derives from CAR 1998; the AD does not, however, reproduce or add to the broader statutory enforcement or administrative procedures contained in CAR 1998.

Incorporation of manufacturer documents

• Bell 212 Maintenance Manual, Section 4 (Revision 5 or later). Requirement 1 makes the maintenance manual a component of the compliance requirement by directing retirement actions to "the times specified in the Mandatory Airworthiness Limitations Schedule, Section 4, of the Bell 212 Maintenance Manual (Revision 5 or later)." This effectively incorporates the relevant portions of the manufacturer’s manual as mandatory regulatory standards for the purposes of this AD.

Interaction with foreign regulatory instruments

• FAA Emergency Airworthiness Directive 2000-15-52. Requirement 2 requires inspection and action "in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52." The AD therefore imports the FAA’s technical instructions into Australian regulatory obligations for the specified mast and trunnion part numbers. The AD acknowledges Bell and FAA cooperation in developing Requirement 2 (Background). That cross-reference creates a link between Australian obligations and US technical standards.

Pre-existing ADs and amendment sequence

• Revocation of Amendment 21. The AD explicitly revokes AD/BELL 212/4 Amdt 21 and replaces it with Amendment 22 (opening paragraph). The Background traces a chain of prior amendments (Amdt 21, Amdt 20, Amdt 19, Amdt 18 and the original 1975 issue). The AD therefore interacts with prior versions by superseding Amdt 21 and by carrying forward prior content that has been reformatted (Requirement 1 reformatted by Amdt 21, Amendment history entries).

Compatibility with maintenance standards and operations

• The AD’s references to the Bell maintenance manual and to the FAA AD create a requirement that operators reconcile Australian regulations with manufacturer and FAA technical procedures. The AD does not otherwise discuss conflicts or mechanisms for reconciling inconsistent instructions; it prescribes a specific manual revision and requires compliance with the FAA AD technical requirements where applicable.

Information disclosure and access

• The AD provides routes to obtain the FAA AD: the FAA internet site (http://av-info.faa.gov/ad) or from the Authority. That instruction establishes a practical interface between Australian operators and the FAA's published materials.

Unstated interactions

• The AD does not explicitly reference certificate conditions, insurance covenants, or employment or contractual obligations that may also be affected by grounding, parts removal or retirement. Those interactions exist in practice but are not spelled out in this instrument.

In sum, AD/BELL 212/4 Amdt 22 operates at the intersection of Australian statutory powers under CAR 1998, manufacturer maintenance materials (Bell Manual Revision 5 or later), and imported FAA technical directives (FAA Emergency AD 2000-15-52). It supersedes and interrelates with prior AD amendments in the Bell 212 AD series.

The AD provides an explicit amendment lineage in the Background section and in the opening paragraph, which is important for tracing the evolution of the current requirements and their technical drivers.

Immediate revocation and issuance

• The opening paragraph states that the CASA delegate "revokes Airworthiness Directive (AD) AD/BELL 212/4 Amdt 21 and issues the following AD under subregulation 39.1(1) of CAR 1998." Amendment 22 therefore supersedes Amendment 21 as of its effective date.

Summary timeline provided in the AD

• Amendment 22 became effective on 9 August 2000 (Compliance and final lines).

• Amendment 21: The Background states that Amendment 21 "added Requirement 2, developed by Bell and the FAA to better control fatigue in the main rotor mast and trunnion following a fatigue-related accident." It further notes that Requirement 1 was reformatted slightly, without technical change and became effective on 28 April 2000. Amendment 22 revokes Amdt 21 and replaces it, while keeping Requirement 2 and updating Requirement 1.

• Amendment 20: Updated the amendment status of the Bell 212 Maintenance Manual. It "became effective on 25 February 1999."

• Amendment 19: "Introduced the Retirement Index Number limitation for the main rotor mast and trunnion," and "became effective on 11 September 1997." That shows the RIN concept has been in the AD series since at least Amendment 19.

• Amendment 18: "Became effective on 5 September 1991." No further detail is provided in this AD on the technical content of Amdt 18.

• Original AD: "The original issue of this Airworthiness Directive became effective on 31 December 1975." This places the initial regulatory action in 1975 and shows periodic amendment in the intervening years.

Technical trigger for the amendment sequence

• The Background describes the immediate technical driver for Amendment 22: a new FAA AD, prompted by the discovery of a cracked main rotor mast. Metallurgical examination showed the crack resulted from fatigue at snap ring groove radii that were smaller than the 0.020 inch minimum allowable dimension. The FAA concluded that corrections to the RIN counting procedure were required. Amendment 21 had earlier added Requirement 2 after a fatigue-related accident; Amendment 22 was issued in response to the FAA AD prompted by another cracked mast and the RIN counting procedure issue.

Administrative sign-off and notification

• The AD is signed by David Alan Villiers, Delegate of the Civil Aviation Safety Authority, on 8 August 2000, and the AD is notified in the Commonwealth of Australia Gazette on 9 August 2000 (final line).

Implications for manual revision

• Requirement 1 references "Bell 212 Maintenance Manual (Revision 5 or later)." Amendment 20 previously updated the amendment status of the Bell manual, effective 25 February 1999, which indicates that the manual revision status has been an explicit consideration in past amendments.

Record of changes

• The AD documents both content changes (e.g., the RIN corrections and added inspections) and formatting changes (Requirement 1 reformatted in Amendment 21). Amendment 22 is presented as a response to new FAA findings while carrying forward prior elements that remain necessary.

For practitioners, the amendment history in this AD is useful for reconstructing the evolution of retirement and inspection obligations: RIN limitations were formally introduced in Amdt 19 (1997), Requirement 2 was added in Amdt 21 (2000) after a fatigue accident, and Amdt 22 (this instrument) was issued in response to a further FAA AD and metallurgical findings, effective 9 August 2000.

The AD document itself contains no record of litigation. The Background and other sections make technical and administrative statements but do not reference any court decisions, appeals, or legal challenges relating to the AD or to the underlying technical findings.

What the AD does record

• The Background documents regulatory and technical events (fatigue-related accident, cracked main rotor mast, metallurgical inspection, FAA conclusions) and the amendment chronology of this AD from the original 1975 issue through Amendment 22. It also notes that Requirement 2 was developed by Bell and the FAA and that FAA AD 2000-15-52 prompted Amendment 22. These are factual or institutional statements, not judicial outcomes.

Absence of litigation references

• There are no references in the AD text to any judicial decisions, Administrative Appeals Tribunal matters, or enforcement proceedings concerning AD/BELL 212/4 or its amendments. The AD does not disclose whether compliance enforcement, disagreements about technical requirements, or any certificates have been litigated.

Implication for research and practice

• Because the AD does not contain litigation history, practitioners seeking to understand any judicial engagement with this AD or its predecessors must look beyond this instrument to external legal databases, tribunal records or CASA enforcement records. The AD itself does not provide any such references, nor does it summarise any appeals or disputes. The only administrative record supplied in the document is the signed issuance by a CASA delegate and the Gazette notification date.

Conclusion on litigation history from source

• Based solely on the text of AD/BELL 212/4 Amendment 22, there is no litigation history recorded in the instrument. The AD presents an administrative and technical narrative but does not assert any court or tribunal encounters.

This AD contains several features and drafting choices that may produce operational surprises or compliance traps if not read carefully.

Incorporation by reference of external technical material

• Requirement 2 requires actions "in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52." The AD does not reproduce those technical requirements. Practitioners must obtain and follow the FAA AD for the full inspection criteria, action thresholds and procedural details. The AD provides a source (FAA website or Authority), but failure to obtain or misinterpret the FAA AD could result in incomplete compliance.

Immediate "before further flight" requirement

• The Compliance paragraph requires that, for Requirement 2 paragraph (a), actions be completed "before further flight after 9 August 2000," unless already accomplished. That is a hard timing hook: if an affected helicopter flew after 9 August 2000 without the paragraph (a) action being done, the operator would have been operating inconsistent with the AD. Practitioners should note which subparagraphs of the FAA AD correspond to paragraph (a) of the Requirement document to avoid missing this urgent hook.

RIN counting corrections and retrospective life reductions

• The Background states the FAA concluded that "several corrections to the RIN counting procedure are required" after discovering that snap ring groove radii were smaller than the 0.020 inch minimum. That means that previously calculated RINs might have been optimistic, and re-calculation using corrected procedures could reduce remaining life unexpectedly. Operators should not assume past RIN accounting is accurate without verification. The AD requires operators to "determine the accumulated Retirement Index Number (RIN)" , that requires careful historical record reconciliation and may indicate earlier work needs re-evaluation.

Parts declared not eligible for Australian service

• The table under Requirement 1 lists several float landing gear crosstube assembly part numbers and marks them "Not eligible for service on Australian helicopters." This is categorical: unlike mere retirement times, this language prohibits those part numbers from Australian service. Operators holding those parts in inventory or planning to import or install them must ensure they are not used on Australian Model 212 helicopters. Misunderstanding "not eligible" as merely discouraged rather than prohibited would be a costly error.

Specified manual revision

• Requirement 1 ties retirement times to "Bell 212 Maintenance Manual (Revision 5 or later)." That phrase locks the baseline to Revision 5 or any later revision, rather than to an earlier revision or to a manual version unspecified. Practitioners must confirm they are using Revision 5 at minimum, because older revisions may contain different limits. Conversely, if a new revision is issued, operators must check whether it is "later" and whether any additional ADs modify that manual reference.

Ambiguity about reporting, records and equivalent means

• The AD does not articulate whether operators may apply for alternative or equivalent compliance paths, nor does it specify reporting or record-keeping obligations triggered by the inspections or retirements. Practitioners should therefore not assume that informal departures from the AD are permissible. Any proposed alternative or repair action should be tested against CASA processes, because the AD itself provides no alternative compliance language.

Subset applicability and hidden risk

• Requirement 2 applies only to helicopters fitted with specified mast or trunnion part numbers. Operators may be unaware of the exact part numbers installed on their aircraft if records are incomplete or if components have been changed. Failing to verify the actual installed part numbers could inadvertently leave a helicopter non-compliant with the immediate "before further flight" requirement.

Interplay with previous amendments

• The AD revokes Amendment 21 and replaces it with Amendment 22. Operators and maintainers who relied on Amendment 21 should ensure they now follow Amendment 22’s content and that any reformatting or reassignments of requirements have not left any practical procedural gaps. The Background notes Requirement 1 was reformatted by Amendment 21 "without technical change" , nevertheless, operators should reconcile any differences between their existing records and the current AD.

Dependency on foreign technical standards

• Dependence on the FAA AD means changes or clarifications from the FAA can affect Australian compliance obligations. Operators must therefore track FAA updates or clarifications for the FAA AD referenced.

Summary of practical gotchas

• Do not assume the AD’s table is exhaustive; check the Bell manual for the full life-limit schedule. Obtain FAA AD 2000-15-52 and map its paragraphs to Requirement 2 in this AD. Recalculate RINs when needed and reconcile historical records. Treat "Not eligible for service on Australian helicopters" as a prohibition. Confirm installed part numbers and manual revision number. Where ambiguity exists, seek the Authority's guidance rather than assuming implied permissions.

The AD prescribes concrete steps required for compliance. The following is a concise, source-grounded compliance checklist derived directly from the text of AD/BELL 212/4 Amendment 22.

1. Identify applicability

   • For Requirement 1, confirm that the aircraft is a Model 212 helicopter (Requirement 1 applicability).
   • For Requirement 2, check whether the helicopter has main rotor mast part number 204-011-450-001, -007, -105, -113, or -119, or main rotor trunnion part number 204-011-105-001 or -103 installed (Requirement 2 applicability).

2. Obtain required documents

   • Obtain a copy of the Bell 212 Maintenance Manual, Revision 5 or later, and locate the Mandatory Airworthiness Limitations Schedule, Section 4 (Requirement 1).
   • Obtain FAA Emergency Airworthiness Directive 2000-15-52. The AD provides two sources: the FAA Internet site (http://av-info.faa.gov/ad) or from the Authority (Note under Requirement 2).

3. Retire components per the manual and AD table

   • For all Model 212 helicopters, retire components at the times specified in the Manual Section 4 (Requirement 1 compliance).
   • In addition, apply the AD’s specific table amendments and exceptions. For the parts listed in the AD table, retire them in accordance with their stated "Retirement Life" hours. Examples from the table:
     • Skid landing gear aft cross tube 205-050-400-035, retire at 500 hours.
     • Skid landing gear aft cross tube 205-050-400-053, retire at 1000 hours.
     • Drive link to rotating swashplate bolts 20-057-5-30D, retire at 500 hours.
   • For the listed float landing gear crosstube assembly part numbers shown as "Not eligible for service on Australian helicopters," do not install those part numbers on Australian Model 212 helicopters (Requirement 1 table).

4. Determine accumulated RIN and inspect mast/trunnion

   • If your helicopter has any of the specified mast or trunnion part numbers, determine the accumulated Retirement Index Number (RIN) for those components (Requirement 2).
   • Perform the inspections and any required actions "in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52" (Requirement 2).

5. Observe timing requirements

   • For Requirement 1, retire components "at the times specified in the Requirement document" (i.e., Manual Section 4 and AD table).
   • For Requirement 2, perform the emergency paragraph actions "before further flight after 9 August 2000" for paragraph (a) of the Requirement document, unless already accomplished. For other actions required by the FAA AD, comply "as specified in the Requirement document."

6. Coordinate maintenance scheduling and parts procurement

   • Anticipate replacement component needs where parts reach prescribed retirement lives.
   • Remove any prohibited float crosstube assembly part numbers from serviceable inventory for Australian helicopters.

7. Reconcile historical records and RIN counting

   • Given the Background’s note that the FAA concluded corrections to RIN counting procedures were required because of dimensional non-conformances (snap ring groove radii smaller than the 0.020 inch minimum), verify historical RIN calculations and update them using the corrected counting procedure as found in FAA AD 2000-15-52 or as instructed by the Authority.

8. Use authorised technical procedures

   • Perform inspections and actions using the technical methods in the Bell Maintenance Manual Revision 5 (or later) and the FAA AD. Do not substitute alternative methods without consulting the Authority or appropriate approvals, because the AD prescribes specific referenced procedures.

9. Obtain authoritative copies and clarifications

   • If the FAA AD text or the manual contains ambiguous instruction, obtain clarification from the Authority. The AD states the FAA AD may be obtained from the FAA Internet site or from the Authority.

10. Record evidence of compliance

• While the AD itself does not stipulate record-keeping specifics, retain documentary proof of the retirement actions, RIN determinations, inspections, and any corrective actions performed in case of regulatory queries and to support airworthiness status.

11. Monitor for additional amendments

• The AD supersedes Amendment 21 and references the iterative amendment history of the AD series. Continue to monitor for further AD amendments or related directives from CASA or the FAA that may alter retirement lives, RIN calculation procedures, or inspection requirements.

12. Grounding implications

• For the "before further flight" actions of Requirement 2 paragraph (a), do not operate the helicopter further until the required RIN determination and the corresponding inspection/action are completed, unless those actions were already completed prior to the effective date.

This is a compliance roadmap derived strictly from the AD text. It prescribes obtaining the specified documents, performing the listed retirement and inspection activities, applying the AD’s table entries and prohibitions, and meeting the timing requirements set out in the Compliance paragraph. Where the AD refers to external technical material (the FAA Emergency AD or the Bell manual), follow those referenced materials for the detailed inspection and action procedures.