Applicability. The AD applies only to Bell Model 212 helicopters fitted with one of the listed spar cap part numbers: P/N 212-030-125-001 with or without retrofit kit P/N 212-704-087 installed; or P/N 212-030-447-001; or P/N 212-030-447-101 (Applicability). The AD explicitly excludes airframes already fitted with spar cap P/N 212-030-447-117 or 212-030-447-117S (Note 1). That identification of parts determines legal reach: an aircraft not fitted with one of the listed P/Ns is outside the AD as written.

Unsafe condition and causal factors. The AD states its basis in reported occurrences: the FAA had received reports of an accident and four failures of the vertical fin spar cap on the same type design. Fatigue cracks were said to originate from rivet holes in fin stations 60-75, with loose rivets, disbonding of doublers and corrosion contributing to cracking (Background). The AD therefore treats cracking, loose fasteners, disbonding and corrosion as the principal failure modes to detect and remedy.

Prescribed corrective and terminating actions. The AD prescribes three levels of action. Requirement 1 sets modification and regular visual inspection for certain P/Ns not modified by a retrofit kit, with initial and recurring intervals. Requirement 2 prescribes more extensive procedures for spar caps already modified by the retrofit kit or for other specific P/Ns, including hammer testing for disbonding and fluorescent penetrant inspection. Requirement 3 prescribes replacement of affected spar caps with the cold expansion P/N 212-030-447-117S, using the Technical Bulletin instructions; Note 2 declares that such replacement is terminating action for further compliance with the AD.

Inspection methods and sources. The AD does not reproduce technical methods; it mandates compliance "in accordance with" specific parts and paragraphs of Bell Helicopter Textron ASB No. 212-00-110 Revision A and Technical Bulletin No. 212-00-184 Revision A (Requirement 1-3). Where the AD specifies hammer tests and fluorescent penetrant inspection these are to be performed in accordance with the referenced ASB parts (Requirement 2b, 2c). In practical terms the ASB/TB provide the step-by-step techniques and acceptance criteria that must be followed.

Timing structure. The AD sets initial, short windows for action measured from 30 October 2002: within 25 hours time in service for many inspections (Compliance 1 and 2a), within 50 hours for some more detailed inspections (Compliance 2b and 2c), and within 24 months for replacement with the cold expansion part (Compliance 3). Recurring intervals vary by procedure: as often as every 8 hours time in service for visual inspections after the initial 25-hour window, and up to 300 hours for fluorescent penetrant/other inspections (Compliance).

Regulatory cross-reference and authority. The AD is issued under CAR 1998 subregulation 39.1(1) (AD header). It also refers to a corresponding FAA AD (Note 3). The instrument carries the signature of a CASA delegate and a Gazette notification date making it an enforceable Australian AD once effective.

Aircraft operators and owners. The primary economic actors affected are the owners and operators of Bell Model 212 helicopters that carry any of the listed spar cap part numbers. The Applicability section identifies precisely which aircraft fall within the AD’s scope: Model 212 helicopters with spar cap P/N 212-030-125-001 (with or without retrofit kit P/N 212-704-087), or P/N 212-030-447-001, or P/N 212-030-447-101. If an operator’s aircraft already has spar cap P/N 212-030-447-117 or 117S installed the AD expressly does not apply (Note 1). Thus the roster of affected aircraft is discrete and determinable by parts identity.

Maintenance organisations and engineers. Licensed maintenance organisations and engineers who perform inspections, modifications, hammer testing, fluorescent penetrant inspections and part replacements will bear the immediate workload of compliance. The AD mandates compliance "in accordance with" specific paragraphs of the Bell ASB and Technical Bulletin; those documents set out procedures, tooling and acceptance criteria that maintenance providers must follow. The AD’s "before further flight" corrective obligations also place responsibility on maintenance to make safe-return-to-service determinations following detection of defects (Requirement 1-2).

Parts suppliers and manufacturers. Suppliers of the specified spar cap parts and the cold expansion part P/N 212-030-447-117S will be affected. Requirement 3 requires replacement using the TB instructions and Attachments A-C; Note 2 makes that replacement terminating action. Where operators elect replacement rather than continuing inspections, demand for the cold expansion spar cap will rise. Bell Helicopter Textron is the manufacturer of the referenced ASB/TB and the P/Ns; the AD invokes their technical materials as mandatory.

Regulator and delegated decision-maker. CASA is the issuing authority; the AD is signed by David Alan Villiers as a delegate of CASA (signature block and date). The AD is issued under CAR 1998 subregulation 39.1(1) and notified in the Commonwealth Gazette, thereby formalising regulatory obligation and the regulator’s direction of maintenance policy for the affected fleet.

Flight operators and scheduling. Operators that use affected Bell 212 helicopters for revenue or non-revenue operations must accommodate the AD’s inspection intervals and any "before further flight" grounding until repairs or replacements occur. The initial and recurring inspections (e.g. initial within 25 hours and recurring every 8 hours for certain visual inspections) will require scheduling adjustments and potential operational downtime.

Safety reporting and compliance resources. The AD references an FAA AD (Note 3) and relies on manufacturer service documents for technical details. Affected parties will need access to those specific ASB/TB Revision A documents to comply. The AD thus affects parts of the compliance chain beyond direct operators: technical documentation holders, procurement channels for parts, and skilled labour to perform specified inspection methods.

Duties imposed by the AD. The AD imposes mandatory duties on owners/operators of applicable Bell 212 helicopters to carry out the specified actions and timings. The core duties are:

• Determine applicability by checking installed spar cap part numbers (Applicability; Note 1).
• Modify and visually inspect spar cap P/N 212-030-125-001 that have not been modified by retrofit kit P/N 212-704-087, in accordance with Part I (A1) paragraphs 1,2,3,4,6 and 7 of ASB No. 212-00-110 Revision A; thereafter perform visual inspections in accordance with Part I (A2) paragraphs 1,2,3,5 and 6 (Requirement 1).
• For spar caps modified by retrofit kit P/N 212-704-087 or for P/N 212-030-447-101, carry out the modification and inspection sequence set out in Part II (A1) paragraphs 1,2,3,4,5,7,8,9 and 10, then perform the recurring visual inspections in Part II (A2) paragraphs 1,2,3,5 and 6 (Requirement 2a).
• Conduct hammer tests to detect disbonding as required in Part II (B) paragraphs 1-13 (Requirement 2b).
• Modify the vertical fin and perform fluorescent penetrant inspection of the spar cap per Part II (C1) paragraphs 1-8 and 10-12, and thereafter recurring fluorescent penetrant inspections per Part II (C2) paragraphs 1-9 and 11-14 (Requirement 2c).
• Repair any loose fasteners or corrosion before further flight, and replace any cracked or disbonded spar cap with a serviceable spar cap before further flight (Requirement 1-2).
• Replace each affected spar cap with cold expansion spar cap P/N 212-030-447-117S in accordance with the Technical Bulletin Accomplishment Instructions and Attachments (Requirement 3).

Timings attached to duties. The AD attaches precise timelines: initial inspections generally within 25 hours time in service after 30 October 2002, with some detailed inspections within 50 hours; recurring inspection intervals are as frequent as every 8 hours for some visual checks and up to 300 hours for penetrant or detailed inspections. Complete replacement with the cold expansion spar cap must occur within 24 months after 30 October 2002 to obtain terminating action (Compliance).

Rights and termination option. The AD creates a clear terminating option: replacement with P/N 212-030-447-117S is stated to be terminating action for further compliance with the AD (Note 2; Requirement 3). That gives owners/operators an explicit compliance pathway that trades an up‑front replacement cost for relief from recurrent inspection burdens. Note 1 creates a further "right" in the sense of an exclusion: if an airframe already has spar cap P/N 212-030-447-117 or 117S installed, the AD does not apply (Note 1).

Corrective timing requirement. The AD repeatedly requires that, where inspection identifies defects (loose fasteners, corrosion, cracked or disbonded spar caps), operators must remedy the defect before further flight (Requirement 1-2). The "before further flight" formulation imposes an operational duty to ground or render unairworthy any helicopter with identified defects until maintenance restores airworthiness.

Prescriptive reference to manufacturer documents. The AD makes compliance contingent upon following specified parts and paragraphs of the Bell ASB and Technical Bulletin (Requirement 1-3). That makes the manufacturer’s instructions part of the legal duty, not merely advisory. Operators must therefore obtain and follow those documents to discharge their obligations.

Authority and issuance. The AD is signed by the CASA delegate and notified in the Gazette, reflecting the regulator’s authority to impose the duties (signature block, Gazette notice). The AD also notes the FAA AD cross-reference (Note 3), which is not a duty under Australian law but may be relevant for operators with obligations under other jurisdictions.

Unspecified enforcement and appeal rights. The AD text does not set out penalties for non-compliance or administrative review/appeal mechanisms. The AD is silent on enforcement procedures or sanctions; it specifies duties and timelines but does not state enforcement pathways or rights of review in the text itself.

Statutory power used. The AD header records that it is issued under subregulation 39.1(1) of CAR 1998. The instrument itself, as printed, sets mandatory maintenance and replacement requirements and makes them effective as of 30 October 2002 (AD header; Compliance). The AD thus rests on the statutory power to issue mandatory airworthiness directives, but the text of the AD does not include a separate enforcement or penalty schedule.

What the AD says about enforcement. The AD does not specify penalties, fines, or enforcement mechanisms within the document. It prescribes mandatory corrective actions, "before further flight" limitations and compliance intervals, but it does not, in this text, state the consequences of failing to comply with the AD. The AD notifies affected persons of the requirements and effective date (30 October 2002) and is signed by a CASA delegate, signalling regulatory force; however penalties are not detailed here.

Implications for operational permissibility. The AD requires that defects (loose fasteners, corrosion, cracked or disbonded spar caps) be repaired or replaced before further flight (Requirement 1-2). Practically this creates immediate operational consequences: an aircraft with an identified defect must not fly until the corrective action is performed, because the AD makes remedial action a condition precedent to further flight. The AD thus creates an immediate safety-driven operational constraint that maintenance must enforce.

Enforcement responsibility and oversight. The AD itself does not name enforcement agents or describe surveillance, audits, or administrative enforcement processes. However, because the AD is a formal CASA instrument signed by a delegate and notified in the Gazette, the CASA regulatory framework and enforcement mechanisms under CAR 1998 and allied regulations would be the relevant enforcement context. The AD text does not reproduce those mechanisms or thresholds.

Cross-jurisdictional coordination. The AD refers to FAA AD 2002-19-05 (Note 3). That cross-reference indicates a parallel FAA action but does not create an enforcement mechanism under Australian law. It may, however, be used operationally by organisations that operate under both jurisdictions or that reference FAA instructions for parts and methods.

Practical enforcement considerations for operators. In practice, compliance will be demonstrated by maintenance records showing that the specified ASB/TB procedures were followed within the prescribed time windows and by documentation of parts replacements where applicable. The AD’s prescriptive references to ASB and TB parts and paragraphs mean that compliance documents must map clearly to those procedures. The AD demands timely corrective action "before further flight", which in practice will be evidenced by maintenance release signatures and logbook entries.

Absence of explicit penalties in the AD. Because the AD does not list penalties, parties looking for enforcement provisions will need to consult the underlying statutory framework (CAR 1998 and associated enforcement provisions) for details about sanctions for non‑compliance. The AD itself is focused on required actions and timings rather than specifying how CASA will enforce compliance in this text.

Statutory basis and regulatory context. The AD is explicitly issued under subregulation 39.1(1) of CAR 1998 as stated in the introductory paragraph. That places the AD within the Civil Aviation Regulations framework. The AD itself does not restate broader obligations under CAR 1998 or other aviation safety legislation, but it is a regulatory instrument deriving its mandate from that subregulation.

Interaction with CASA processes and documentation. The AD incorporates manufacturer service documents,Bell ASB No. 212-00-110 Revision A and Bell Technical Bulletin No. 212-00-184 Revision A,by reference as mandatory procedures (Requirement 1-3). This makes the manufacturer’s service instructions legally consequential under the AD. Operators must therefore reconcile the AD’s requirements with existing maintenance manuals, approved data, and continuing airworthiness management procedures required by the broader regulatory regime. The AD does not itself resolve conflicts between manufacturer instructions and other approved data; it directs compliance with particular ASB/TB paragraphs.

Cross-reference to foreign airworthiness directive. The AD explicitly refers to FAA AD 2002-19-05 Amdt 39-12885 (Note 3). That cross-reference indicates a related FAA action addressing the same unsafe condition. For operators subject to multiple jurisdictions (for example, Australian operators flying internationally, or foreign-registered aircraft operating in Australia), the AD suggests parallel compliance considerations, but it does not abrogate or supersede obligations under foreign jurisdictions. The AD applies within the Australian regulatory regime and takes effect via Gazette notification.

Effect on airworthiness approvals and maintenance release. The AD enforces actions that must be completed in accordance with the specified ASB/TB for the aircraft to be considered compliant with this AD. Those actions will interact with the normal processes of maintenance release, certificates of airworthiness, and continuing airworthiness obligations. The AD does not alter the existing processes but becomes part of the set of mandatory maintenance actions that must be satisfied for legal airworthiness.

Interaction with parts and modifications approvals. The AD mandates replacement with a specific P/N (212-030-447-117S) using Bell Technical Bulletin procedures (Requirement 3). Where modifications or alternative means of compliance are contemplated, the AD text does not provide an alternative approval route within the document; operators would need to seek any deviations or alternative methods of compliance through the relevant regulatory channels established by CASA (not specified in the AD). Therefore, any deviations would have to be reconciled with the broader CAR 1998 approval processes.

Publication and legal effect. The AD was notified in the Commonwealth of Australia Gazette on 30 October 2002, making the instrument formally known and effective in the Commonwealth’s official publication (Gazette notice). The AD’s legal effect is therefore cemented by both the CASA delegate’s signature and Gazette notification. The AD itself does not, however, canvass appeal, relief or variation procedures; those procedural avenues would be found in the wider legislative and regulatory framework rather than in the AD text.

No express interaction with commercial law or insurance in the AD text. The AD does not address commercial contracts, insurance coverage, or liability allocation. The AD’s operational effects,inspection intervals, grounding until repairs,will have practical commercial impacts, but the AD does not alter contractual or insurance frameworks within its text.

Effective date and versioning. The AD became effective on 30 October 2002, as stated in the Compliance section and confirmed by the Gazette notification line. The signing delegate dated the document 24 October 2002 (signature block). The published AD references specific revisions of manufacturer service documents: Bell ASB No. 212-00-110 Revision A dated 15 February 2001 and Bell Helicopter Textron Technical Bulletin No. 212-00-184 Revision A dated 23 April 2001 (Requirement 1-3). The AD text itself is labelled AD/BELL 212/64 Vertical Fin Spar 13/2002 DM.

No in-document amendments or later revisions listed. The AD text provides no history of amendments, superseding ADs, or subsequent revisions to the AD within the document. It does not state any amendment dates, revocations, or modifications to the AD text. Consequently, within this document there is no recorded internal amendment history beyond the initial issuance and effective date.

References to earlier or parallel actions. The AD references FAA AD 2002-19-05 (Note 3). That cross-reference connects the Australian AD to a corresponding FAA action, but the AD does not state that it amends or is superseded by that FAA AD; it simply refers to it. The AD also incorporates Revision A of the manufacturer’s ASB and Technical Bulletin, which are earlier manufacturer-issued revisions; the AD does not itself author new technical methods but makes those manufacturer revisions mandatory for compliance. The AD does not provide an explicit timeline of prior ADs on this subject beyond this linkage.

No later consolidations recorded here. The document contains no notation such as "supersedes AD No. X" or "amended by AD No. Y". Users seeking to confirm whether the AD has been amended, superseded or revoked after the effective date must consult CASA’s consolidated AD listings or subsequent Gazette notices; the AD text itself includes no post‑issuance amendment entries.

Implication of "DM" suffix. The AD is labelled with "DM" in its heading (AD/BELL 212/64 ... DM). The AD text does not define "DM" or explain whether it denotes a document type, classification, or administrative mark. The AD body similarly contains no further metadata about versioning beyond the manufacturer document Revision A references and the effective/Gazette dates.

Takeaway for users. The AD, as presented, is a single-issue directive issued in October 2002, incorporating specific manufacturer revisions and containing no internal amendment history. Users who require the current legal position or any subsequent amendments should consult CASA’s current AD database or later Gazette notices to establish whether this AD has been modified, superseded, or revoked after publication.

No litigation recorded in the AD. The AD text contains no references to litigation, judicial review, dispute resolutions, or case law. It does not cite any court decisions, administrative tribunal findings, or challenges to the AD’s validity or content.

No indications of enforcement proceedings within the document. The AD sets mandatory obligations but does not report any prosecutions, enforcement actions, or civil proceedings arising from non‑compliance. The document is a regulatory directive and does not include a litigation log.

Relevant background incidents referenced. The AD records that the FAA had received reports of an accident and four failures of the vertical fin spar cap, citing those occurrences as the basis for the AD (Background). Those incident reports are the factual foundation for the AD’s safety rationale, but the AD does not characterise them as litigated matters. No mention is made of civil claims, liability, or insurance disputes connected to those accidents or failures in the AD text.

Cross-reference to FAA action, not litigation. The AD refers to FAA AD 2002-19-05 (Note 3) as a related action. That is an administrative action by the FAA, not a court judgment. The AD does not report any legal challenges to the FAA AD nor does it claim that litigation exists as to the underlying incidents.

Practical note for researchers. If lawyers or researchers require a litigation history related to the events motivating this AD (the accident and spar cap failures) or to the AD’s implementation, that information is not contained in the AD. It would need to be sought from court registries, incident investigation reports, or CASA and FAA enforcement records outside of the AD document. The AD itself does not provide entries or references to any subsequent judicial or administrative litigation.

Narrow applicability determined by part numbers. The AD applies only to Model 212 helicopters with specific spar cap P/Ns: 212-030-125-001 (with or without retrofit kit P/N 212-704-087 installed), 212-030-447-001, or 212-030-447-101 (Applicability). Operators should not assume the AD applies to all Model 212 aircraft; applicability is part-number specific. Conversely, if the installed spar cap is P/N 212-030-447-117 or 117S the AD explicitly does not apply (Note 1). Accurate parts identification is therefore decisive.

Terminating action incentive and timing. Replacement with cold expansion spar cap P/N 212-030-447-117S is defined as terminating action for further compliance with the AD (Note 2; Requirement 3). That creates a clear trade-off: bear up-front replacement cost and administrative burden of that modification once (within 24 months) to eliminate ongoing inspection burdens (which for some items are as frequent as every 8 hours time in service). Operators must calculate the comparative costs of recurrent inspections and operational disruption versus replacement.

Short recurring inspection intervals. For certain configurations the AD requires visual inspections at intervals not to exceed 8 hours time in service after an initial 25‑hour window (Compliance 1 and 2a). An 8‑hour interval can translate into inspections before each flight day or even more frequently depending on duty cycles, thereby increasing maintenance workload and potential flight cancellations if defects are found. These short intervals are operationally significant and can be overlooked if scheduling is not adjusted.

Multiple inspection methods and referenced paragraphs. The AD does not prescribe full technical steps within its text; it requires compliance "in accordance with" specified parts and paragraphs of the Bell ASB and Technical Bulletin (Requirements). Operators must obtain those exact ASB/TB revisions (ASB No. 212-00-110 Revision A and TB No. 212-00-184 Revision A) and follow the particular paragraphs cited (e.g. Part II (B) paragraphs 1-13 for hammer testing). Failure to follow the exact cited paragraphs could be considered non‑compliance even if similar methods are used.

"Before further flight" immediacy. The AD requires that loose fasteners or corrosion be repaired and cracked or disbonded spar caps be replaced "before further flight" (Requirement 1-2). That phrasing imposes an immediate operational constraint: an aircraft may not be flown if it fails inspection for those criteria. Practically, that can lead to urgent part procurement, grounding and schedule disruption.

Multiple compliance windows. Different inspection tasks have different initial compliance windows: some must be done within 25 hours after 30 October 2002, others within 50 hours, with recurring intervals varying between 8 hours and 300 hours (Compliance). Operators must track each inspection task separately to ensure compliance timelines are met.

Reference to FAA AD but no cross-certification in text. The AD refers to FAA AD 2002-19-05 (Note 3). That reference can be useful for cross-checking technical rationale, but the AD does not adopt the FAA AD into Australian law; it stands on its own regulatory footing. Users should not assume the FAA AD’s procedural differences or reliefs are automatically available under this AD.

No penalties or enforcement details included. The AD does not state enforcement processes or penalties; it is silent on those points. Operators cannot find enforcement consequences in the AD text and must instead consult CAR 1998 and CASA guidance for enforcement details.

Absence of alternative compliance pathways in text. The AD establishes mandatory actions and does not set out any alternative means of compliance within the document. Any desire to pursue an alternative method or deviating modification will require engagement with CASA under the general regulatory framework, as the AD text itself does not grant alternatives.

Step 1 , Establish applicability. Examine the helicopter’s tailboom/spar cap part number. The AD applies only if the installed spar cap is P/N 212-030-125-001 (with or without retrofit kit P/N 212-704-087), P/N 212-030-447-001, or P/N 212-030-447-101 (Applicability). If the spar cap is P/N 212-030-447-117 or 212-030-447-117S, the AD does not apply (Note 1).

Step 2 , Obtain referenced documents. The AD mandates specific compliance procedures "in accordance with" Bell Helicopter Textron ASB No. 212-00-110 Revision A dated 15 February 2001 and Technical Bulletin No. 212-00-184 Revision A dated 23 April 2001 (Requirement 1-3). Acquire these exact Revision A documents and the specific Parts/paragraphs cited in the AD (for example, Part I (A1)/(A2), Part II (A1)/(A2)/(B)/(C1)/(C2), and Technical Bulletin Accomplishment Instructions and Attachments A-C). Operators must follow the exact paragraphs referenced.

Step 3 , Perform initial required modifications and inspections within time windows. Follow the applicable sequences and initial deadlines:

• For P/N 212-030-125-001 not modified by retrofit kit: modify and visually inspect as per Part I (A1) paragraphs 1,2,3,4,6,7 of the ASB within 25 hours time in service after 30 October 2002 (unless already done), and thereafter perform the listed visual inspections per Part I (A2) at intervals not to exceed 8 hours time in service (Requirement 1; Compliance 1).

• For P/N 212-030-125-001 modified by retrofit kit P/N 212-704-087, or spar cap P/N 212-030-447-101: perform modification and inspections per Part II (A1) paragraphs 1-5,7-10 within 25 hours, then recurring visual inspections per Part II (A2) at intervals not to exceed 8 hours (Requirement 2a; Compliance 2a). Perform hammer testing for disbonding in accordance with Part II (B) paragraphs 1-13 within 50 hours and then at intervals not greater than 300 hours where required (Requirement 2b; Compliance 2b). Modify the vertical fin and fluorescent penetrant inspect per Part II (C1) paragraphs 1-8 and 10-12 within 50 hours, and thereafter fluorescent penetrant inspect per Part II (C2) paragraphs 1-9 and 11-14 at intervals not exceeding 300 hours (Requirement 2c; Compliance 2c).

Step 4 , Immediate corrective actions. If any inspection detects loose fasteners or corrosion, repair them before further flight. If any inspection detects cracked or disbonded spar caps, replace the spar cap with a serviceable unit before further flight (Requirement 1-2). Document all repairs and replacements in maintenance records and the aircraft logbook, mapping entries to the specific ASB/TB paragraphs executed.

Step 5 , Consider terminating replacement. Within 24 months after 30 October 2002 replace each affected spar cap with the cold expansion spar cap P/N 212-030-447-117S in accordance with the Technical Bulletin Accomplishment Instructions and Attachments (Requirement 3; Compliance 3). Note that such replacement is terminating action for further compliance with the AD (Note 2). If replacement is already present (P/N 212-030-447-117 or 117S), no further action under this AD is required (Note 1).

Step 6 , Record-keeping and evidence of compliance. Maintain records that link performed actions to the AD requirements and to the ASB/TB paragraphs referenced. Include dates, time in service at the time of inspection, findings (including none found), corrective actions taken "before further flight", part numbers of replaced components, and the details of persons or organisations performing the work. These records will be necessary to demonstrate compliance and for any regulatory inspection or audit by CASA.

Step 7 , Scheduling and operational planning. Because some inspections recur at intervals as short as every 8 hours time in service, plan operational cycles and maintenance windows to ensure inspections are performed without disrupting commercial or other flight obligations. If defects are found, immediate grounding until repair or replacement is required.

Step 8 , Procurement and logistics. If electing the terminating replacement route, source the cold expansion spar cap P/N 212-030-447-117S and any parts and tooling called for by the Technical Bulletin. Alternatively, ensure stock of serviceable spar caps and consumables for recurring inspections and repairs so "before further flight" obligations can be met promptly.

Step 9 , Liaise with CASA for alternatives or clarification. The AD does not provide alternative methods of compliance within the text. If operators believe an alternative means of compliance or deviation is necessary, engage with CASA under the statutory processes established by CAR 1998 for relief or variations to mandatory ADs (the AD text itself does not set out those processes).

Step 10 , Cross-reference FAA AD and coordinate where relevant. The AD refers to FAA AD 2002-19-05 (Note 3). If operations involve multiple jurisdictions or if additional FAA procedures or parts data are relevant, cross-check the FAA AD to ensure consistency of actions across operational responsibilities, while recognising the Australian AD is the determinative legal requirement in Australia.

Document and timeline checklist (practical). For immediate compliance actions after the effective date of 30 October 2002:

• Within 25 hours TIS: complete the initial modification and visual inspections per relevant ASB Part I or II for applicable P/Ns.
• Thereafter: perform visual inspections at intervals not to exceed 8 hours TIS where specified.
• Within 50 hours TIS: perform hammer testing and fluorescent penetrant inspections as required for modified spar caps or specified P/Ns.
• Thereafter: perform hammer and penetrant inspections at intervals not to exceed 300 hours TIS where specified.
• Within 24 months: complete replacement with the cold expansion spar cap P/N 212-030-447-117S to terminate AD obligations.

Following these steps and documenting actions against the exact ASB/TB paragraphs cited in the AD will align operator practices with the AD’s mandatory requirements.